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TRANSCRIPT
SIEMENSSIEMENSSIEMENS
NX Nastran 11Verification Manual
Contents
Proprietary & Restricted Rights Notice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
Overview of the Verification Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1Running the Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
Linear Statics Verification Using Theoretical Solutions . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
Overview of Linear Statics Verification Using Theoretical Solutions . . . . . . . . . . . . . . . . . . . . 2-1Understanding the Test Case Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1Understanding Comparisons with Theoretical Solutions . . . . . . . . . . . . . . . . . . . . . . . . . 2-2References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3Point Load on a Cantilever Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3Axial Distributed Load on a Linear Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4Distributed Loads on a Cantilever Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Moment Load on a Cantilever Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7Edge Pressure on Beam Element - Torque Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Thermal Strain, Displacement, and Stress on Heated Beam . . . . . . . . . . . . . . . . . . . . . 2-11Uniformly Distributed Load on Linear Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13Membrane Loads on a Linear Quadrilateral Thin Shell Element . . . . . . . . . . . . . . . . . . . 2-14Axial Loading on Rod Element . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16Stress on a Beam as It Expands and Closes a Gap . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18Thin Wall Cylinder in Pure Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19Thin-walled Cantilever Beam in Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21Strain Energy of a Truss . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23
Linear Statics Verification Using Standard NAFEMS Benchmarks . . . . . . . . . . . . . . . . . . 3-1
Overview of Linear Statics Verification Using Standard NAFEMS Benchmarks . . . . . . . . . . . . . 3-1Understanding the Test Case Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2Elliptic Membrane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2Cylindrical Shell Patch Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6Hemisphere-Point Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9Z-Section Cantilever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11Skew Plate Normal Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13Thick Plate Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15Solid Cylinder/Taper/Sphere — Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19
Normal Mode Dynamics Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
Overview of Normal Mode Dynamics Verification Using Theoretical Solutions . . . . . . . . . . . . . 4-1
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Understanding the Test Case Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1Understanding Comparisons with Theoretical Solutions . . . . . . . . . . . . . . . . . . . . . . . . . 4-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2
Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2Undamped Free Vibration — Single Degree of Freedom . . . . . . . . . . . . . . . . . . . . . . . . . 4-2Two Degrees of Freedom Undamped Free Vibration — Principle Modes . . . . . . . . . . . . . . 4-4Three Degrees of Freedom Torsional System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6Two Degrees of Freedom Vehicle Suspension System . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8Two Degrees of Freedom Vehicle Suspension System . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9Cantilever Beam Undamped Free Vibrations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11Natural Frequency of a Cantilevered Mass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks . . . . . . . . . . . 5-1
Overview of Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks . . . . . 5-1Understanding the Test Case Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1
Beam Element Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2Pin-ended Cross — In-plane Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2Pin-ended Double Cross - In-plane Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-4Free Square Frame - In-plane Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7Cantilever with Off-center Point Masses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9Deep Simply-Supported Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10Circular Ring — In-plane and Out-of-plane Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12Cantilevered Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14
Shell Element Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-16Thin Square Cantilevered Plate — Symmetric Modes . . . . . . . . . . . . . . . . . . . . . . . . . . 5-16Thin Square Cantilevered Plate — Anti-symmetric Modes . . . . . . . . . . . . . . . . . . . . . . . 5-19Free Thin Square Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-22Simply Supported Thin Square Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-24Simply Supported Thin Annular Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-26Clamped Thin Rhombic Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-28Cantilevered Thin Square Plate with Distorted Mesh . . . . . . . . . . . . . . . . . . . . . . . . . . 5-31Simply Supported Thick Square Plate, Test A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-35Simply Supported Thick Square Plate, Test B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-37Clamped Thick Rhombic Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-40Simply Supported Thick Annular Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-43Cantilevered Square Membrane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-46Cantilevered Tapered Membrane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-48Free Annular Membrane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-51Cantilevered Thin Square Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-54
Axisymmetric Solid and Solid Element Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-57Free Cylinder — Axisymmetric Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-57Thick Hollow Sphere — Uniform Radial Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-59Simply Supported Annular Plate — Axisymmetric Vibration . . . . . . . . . . . . . . . . . . . . . . 5-62Deep Simply Supported "Solid" Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-65Simply Supported "Solid" Square Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-69Simply Supported "Solid" Annular Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-72Cantilevered Solid Beam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-76
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Contents
Verification Test Cases from the Societe Francaise des Mecaniciens . . . . . . . . . . . . . . . . 6-1
Overview of Verification Test Cases Provided by the Societe Francaise des Mecaniciens . . . . . 6-1Understanding the Test Case Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1
Mechanical Structures — Linear Statics Analysis with Beam or Rod Elements . . . . . . . . . . . . . 6-2Short Beam on Two Articulated Supports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2Clamped Beams Linked by a Rigid Element . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3Transverse Bending of a Curved Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5Plane Bending Load on a Thin Arch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-8Grid Point Load on an Articulated CONROD Truss . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-10Articulated Plane Truss . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-13Beam on an Elastic Foundation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16
Mechanical Structures — Linear Statics Analysis with Shell Elements . . . . . . . . . . . . . . . . . 6-19Plane Shear and Bending Load on a Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-19Infinite Plate with a Circular Hole . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21Uniformly Distributed Load on a Circular Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-24Torque Loading on a Square Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-26Cylindrical Shell with Internal Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-28Uniform Axial Load on a Thin Wall Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-32Hydrostatic Pressure on a Thin Wall Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-35Pinched Cylindrical Shell . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-38Spherical Shell with a Hole . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-40Bending Load on a Cylindrical Shell . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-43Uniformly Distributed Load on a Simply-Supported Rectangular Plate . . . . . . . . . . . . . . . 6-46Uniformly Distributed Load on a Simply-Supported Rhomboid Plate . . . . . . . . . . . . . . . . 6-49Shear Loading on a Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Mechanical Structures — Linear Statics Analysis with Solid Elements . . . . . . . . . . . . . . . . . 6-54Solid Cylinder in Pure Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-54Internal Pressure on a Thick-Walled Spherical Container . . . . . . . . . . . . . . . . . . . . . . . 6-60Internal Pressure on a Thick-Walled Infinite Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . 6-65Prismatic Rod in Pure Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-70Thick Plate Clamped at Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-74
Mechanical Structures — Normal Mode Dynamics Analysis . . . . . . . . . . . . . . . . . . . . . . . . 6-79Lumped Mass-Spring System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-79Short Beam on Simple Supports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-82Axial Loading on a Rod . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-85Cantilever Beam with a Variable Rectangular Section . . . . . . . . . . . . . . . . . . . . . . . . . . 6-87Thin Circular Ring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-89Thin Circular Ring Clamped at Two Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-92Vibration Modes of a Thin Pipe Elbow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-95Cantilever Beam with Eccentric Lumped Mass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-98Thin Square Plate (Clamped or Free) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-101Simply-Supported Rectangular Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-103Thin Ring Plate Clamped on a Hub . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-105Vane of a Compressor - Clamped-free Thin Shell . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-108Bending of a Symmetric Truss . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-111Hovgaard's Problem — Pipes with Flexible Elbows . . . . . . . . . . . . . . . . . . . . . . . . . . 6-114Rectangular Plates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-117
Mechanical Structures — Normal Mode Dynamics Analysis and Model Response . . . . . . . . 6-120
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Contents
Transient Response of a Spring-Mass System with Acceleration Loading . . . . . . . . . . . 6-120Transient Response of a Clamped-free Post . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-123
Stationary Thermal Tests — Heat Transfer Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-126Hollow Cylinder - Fixed Temperatures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-126Hollow Cylinder - Convection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-129Cylindrical Rod - Flux Density . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-131Hollow Cylinder with Two Materials - Convection . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-133Wall-Convection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-136Wall-Fixed Temperatures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-138L-Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-140Orthotropic Square . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-142Hollow Sphere - Fixed Temperatures, Convection . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-145Hollow Sphere with Two Materials - Convection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-148
Thermo-mechanical Tests — Linear Statics Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-152Orthotropic Cube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-152Thermal Gradient on a Thin Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-155Simply-Supported Arch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-158
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks . . . . . . . 7-1
Overview of the Material Nonlinear (Plasticity) Verification Using NAFEMS Test Cases . . . . . . . 7-1Understanding the Verification Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1
Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2Plane Strain Elements - Perfect Plasticity Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2Plane Strain Elements - Isotropic Hardening Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-6Plane Stress Elements - Perfect Plasticity Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-10Plane Stress Elements - Isotropic Hardening Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-14Solid Element - Perfect Plasticity Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18Solid Element - Isotropic Hardening Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks . . . . . . . . . . . . . 8-1
Overview of the Geometric Nonlinear Verification Using NAFEMS Test Cases . . . . . . . . . . . . . 8-1Understanding the Verification Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1
Test Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2Straight Cantilever with End Moment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2Straight Cantilever with Axial End Point Load - Brick Elements . . . . . . . . . . . . . . . . . . . . 8-6Straight Cantilever with Axial End Point Load - BEAM Elements . . . . . . . . . . . . . . . . . . 8-11Lee's Frame Buckling Problem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-15Large Displacement Elastic Response of a Hinged Spherical Shell Under Uniform PressureLoading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-18
Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-21Reference . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-21
6 NX Nastran 11 Verification Manual
Contents
Proprietary & Restricted Rights Notice
© 2016 Siemens Product Lifecycle Management Software Inc. All Rights Reserved.
This software and related documentation are proprietary to Siemens Product Lifecycle ManagementSoftware Inc. Siemens and the Siemens logo are registered trademarks of Siemens AG. NX is atrademark or registered trademark of Siemens Product Lifecycle Management Software Inc. or itssubsidiaries in the United States and in other countries.
NASTRAN is a registered trademark of the National Aeronautics and Space Administration. NXNastran is an enhanced proprietary version developed and maintained by Siemens Product LifecycleManagement Software Inc.
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All other trademarks are the property of their respective owners.
TAUCS Copyright and License
TAUCS Version 2.0, November 29, 2001. Copyright (c) 2001, 2002, 2003 by Sivan Toledo, Tel-AvivUniversity, [email protected]. All Rights Reserved.
TAUCS License:
Your use or distribution of TAUCS or any derivative code implies that you agree to this License.
THIS MATERIAL IS PROVIDED AS IS, WITH ABSOLUTELY NO WARRANTY EXPRESSED ORIMPLIED. ANY USE IS AT YOUR OWN RISK.
Permission is hereby granted to use or copy this program, provided that the Copyright, this License,and the Availability of the original version is retained on all copies. User documentation of any codethat uses this code or any derivative code must cite the Copyright, this License, the Availability note,and "Used by permission." If this code or any derivative code is accessible from within MATLAB, thentyping "help taucs" must cite the Copyright, and "type taucs" must also cite this License and theAvailability note. Permission to modify the code and to distribute modified code is granted, providedthe Copyright, this License, and the Availability note are retained, and a notice that the code wasmodified is included. This software is provided to you free of charge.
Availability (TAUCS)
As of version 2.1, we distribute the code in 4 formats: zip and tarred-gzipped (tgz), with or withoutbinaries for external libraries. The bundled external libraries should allow you to build the testprograms on Linux, Windows, and MacOS X without installing additional software. We recommendthat you download the full distributions, and then perhaps replace the bundled libraries by higherperformance ones (e.g., with a BLAS library that is specifically optimized for your machine). If youwant to conserve bandwidth and you want to install the required libraries yourself, download thelean distributions. The zip and tgz files are identical, except that on Linux, Unix, and MacOS,unpacking the tgz file ensures that the configure script is marked as executable (unpack with tarzxvpf), otherwise you will have to change its permissions manually.
NX Nastran 11 Verification Manual 7
Chapter 1: Introduction
1.1 Overview of the Verification ManualThis guide contains verification test cases for NX Nastran. These test cases verify the function ofthe different NX Nastran analysis types using theoretical and benchmark solutions from well-knownengineering test cases. Each test case contains test case data and information, such as element typeand material properties, results, and references.
The guide contains test cases for:
• Linear Statics verification using theoretical solutions
• Linear Statics verification using standard NAFEMS benchmarks
• Normal Mode Dynamics verification using theoretical solutions
• Normal Mode Dynamics verification using standard NAFEMS benchmarks
• Verification Test Cases from the Societe Francaise des Mecaniciens
• Material Nonlinear (Plasticity) verification using standard NAFEMS benchmarks (NX Nastranonly)
• Geometric Nonlinear verification using standard NAFEMS benchmarks
1.2 Running the Test CasesAll verification test cases are available as *.dat files and are included in the NX Nastran installationin the directory path install_dir/NXr/nast/demo.
The test cases are relatively simple, and most have closed-form theoretical solutions. Differencesbetween finite element and theoretical solutions are in most cases negligible. Some tests wouldrequire an infinite number of elements to achieve an exact solution. Elements are chosen to achievereasonable engineering accuracy with reasonable computing times.
Note
Actual results from NX Nastran may vary insignificantly from the results presented in thisdocument. This variation is generally due to different methods of performing real numberalgorithms on different systems.
NX Nastran 11 Verification Manual 1-1
Chapter 2: Linear Statics Verification UsingTheoretical Solutions
2.1 Overview of Linear Statics Verification Using TheoreticalSolutionsThe purpose of these linear statics test cases is to verify the function of the NX Nastran softwareusing theoretical solutions. The test cases are relatively simple in form and most of them haveclosed-form theoretical solutions.
The theoretical solutions shown in these examples are from well-known engineering texts. For eachtest case, a specific reference is cited. All theoretical reference texts are listed at the end of this topic.
The finite element method is very flexible in the types of physical problems represented. Theverification tests provided are not exhaustive in exploring all possible problems, but representcommon types of applications.
This overview provides information on the following:
• Understanding the test case format
• Understanding comparisons with theoretical solutions
• References
Understanding the Test Case Format
Each test case is structured with the following information.
• Test case data and information:
o Physical and material properties
o Finite element modeling (modeling procedure or hints)
o Units
o Solution type
o Element type
o Boundary conditions (loads, restraints)
• Results
• References (text from which a closed-form or theoretical solution was taken)
In addition to these example problems, test cases from NAFEMS (National Agency for Finite ElementMethods and Standards, National Engineering Laboratory, Glasgow, U.K.) have been executed.
NX Nastran 11 Verification Manual 2-1
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Results for these test cases can be found in the next section, Linear Statics Analysis VerificationUsing NAFEMS Standard Benchmarks.
Understanding Comparisons with Theoretical Solutions
While differences in finite element and theoretical results are, in most cases, negligible, some testswould require an infinite number of elements to achieve the exact solution. Elements are chosen toachieve reasonable engineering accuracy with reasonable computing times.
Results reported here are results which you can compare to the referenced theoretical solution.Other results available from the analyses are not reported here. Results for both theoretical and finiteelement solutions are carried out with the same significant digits of accuracy.
The closed-form theoretical solution may have restrictions, such as rigid connections, that do notexist in the real world. These limiting restrictions are not necessary for the finite element model, butare used for comparison purposes. Verification to real world problems is more difficult but should bedone when possible.
The actual results from the NX Nastran software may vary insignificantly from the results presented inthis document. This variation is due to different methods of performing real numerical arithmetic ondifferent systems. In addition, it is due to changes in element formulations which have been made toimprove results under certain circumstances.
References
The following references have been used in the Linear Statics Analysis verification problemspresented:
1. Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992.
2. Harris, C. O. Introduction to Stress Analysis. New York Macmillan1959.
3. Roark, R. and Young, W. Formulas for Stress and Strain, 5th Edition. New York: McGraw-HillBook Company, 1975.
4. Shigley, J. and Mitchel L. Mechanical Engineering Design, 4th Edition. New York: McGraw-HillBook Company, 1983.
5. Timoshenko, S. Strength of Materials, Part I, Elementary Theory and Problems. New YorK: VanNorstrand Reinhold Company, 1955.
2-2 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Test Cases
Point Load on a Cantilever Beam
Determine the deflection of a beam at the free end. Determine the stress at the midpoint of the beam.
Test Case Data and Information
Input Files
mstvl001.dat
Units
Inch
Model Geometry
Length = 480 in.
Cross Sectional Properties
• Area = 30 x 30 in.
• Iy = Iz = 67500 in.4
NX Nastran 11 Verification Manual 2-3
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Material Properties
• E = 30E06 psi
Finite Element Modeling
Create four successive linear beam (CBAR) elements along the X axis.
Boundary Conditions
• Restraints
o Restrain the left end of the beam in all six degrees.
• Loads
o Set grid force to 50,000 lb in. the -Y direction.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranVon Mises Stress, grid point 1 (psi) 5333. 5333.Y Deflection, grid point 5 (in) 0.9102 0.9130
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 716.
Axial Distributed Load on a Linear Beam
Determine the stress, elongation and resultant force due to an axial loading along a linear beam
element.
Test Case Data and Information
Input Files
mstvl002.dat
2-4 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Units
Inch
Model Geometry
• Length = 300 in.
Cross Sectional Properties
• Area = 9 in.2
• square cross section (3 in. x 3 in.)
Material Properties
• E = 30E+6 psi
Finite Element Modeling
Create 30 beam element along the X axis, each 10 in. long.
Boundary Conditions
• Restraints
o Restrain one end of the beam in all six degrees.
• Loads
o Apply the axial force as an axial distributed load (force per unit length) of 1000 lb/in. to the 10in. long element furthest from the restrained end.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranVon Mises Stress, grid point 1 (psi) 1111. 1111.
NX Nastran 11 Verification Manual 2-5
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Result Bench Value NX NastranDeflection in X, grid point 2 (in) 0.01111 0.01093Reaction in X, grid point 1 (lb) –1.000E4 –1.000E4
References
Beer and Johnston. Mechanics of Materials.. New York: McGraw-Hill, Inc., 1992. p. 76.
Distributed Loads on a Cantilever Beam
Determine the deflection of a beam at the free end. Determine the stress at the midpoint of thebeam and the reaction force at the restrained end.
Test Case Data and Information
Input Files
mstvl003.dat
Units
Inch
Model Geometry
Length = 480 in.
Cross Sectional Properties
• Area = 900 in.2
• Square cross section (30 in. x 30 in.)
• Iy = Iz = 67500 in.4
2-6 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Material Properties
• E = 30E06 psi
Finite Element Modeling
Create eight successive linear beam (CBAR) elements along the X axis.
Boundary Conditions
• Restraints
o Restrain the left end of the beam in all six degrees.
• Loads
o Define a distributed load of 250 lb/in. in the –Y direction.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranX Stress at grid point 1 (psi) 6,400. 6,383.Deflection Magnitude at grid point 5 (in) 0.8190 0.8225 *Reaction Force Magnitude at grid point 1 (lb) 1.200E5 1.200E5
* Includes shear deformation which is neglected in theoretical value.
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 716.
Moment Load on a Cantilever Beam
Determine the deflection of a beam at the free end. Determine the bending stress of the beam andthe reaction force at the restrained end.
NX Nastran 11 Verification Manual 2-7
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl004.dat
Units
Inch
Model Geometry
Length = 480 in.
Cross Sectional Properties
• Square cross section 30” x 30” inches
• Area = 900 in.2
• Iy = Iz = 67500 in.4
Material Properties
• E = 30E6 psi
Finite Element Modeling
Create eight successive linear beam (CBAR) elements along the X axis.
Boundary Conditions
• Restraints
o Restrain the left end of the beam in all six degrees.
• Loads
2-8 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
o Set the Z-moment of the end grid point to 2.5E6 in.-lb.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranVon Mises Stress at grid point 1 (psi) 555.6 555.6Deflection Magnitude at grid point 5 (in) 0.1422 0.1422Reaction Moment Z Direction at grid point 1(in.-lb)
2.500E6 2.499E6
* Includes shear deformation which is neglected in theoretical value.
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 716.
Edge Pressure on Beam Element - Torque Loading
Determine the stress, elongation and resultant force due to a torque applied to a hollow cylinderat the free end.
NX Nastran 11 Verification Manual 2-9
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl005.dat
Units
SI - meter
Model Geometry
Length = 1.5 m
Cross Sectional Properties
• Radius1 = 0.02 m
• Radius2 = .03 m
Material Properties
• E = 208.6 GPa
Finite Element Modeling
• Create a CBAR element along the X axis.
• To find the maximum shearing stress, set the effective radius in torsion to 0.03 m.
• The minimum shearing stress is located at a radius equal to 0.02 m.
Boundary Conditions
• Restraints
o Restrain the left end of the beam in all six degrees.
• Loads
o Apply an edge torque equal to 4.08 kN-m along the 10 cm linear beam (CBAR) elementfurthest from the restrained end.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranMax Torsional Shear Stress (MPa) 120.0 120.0
Min Torsional Shear Stress (MPa) 80.00 80.00
2-10 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Post Processing
To obtain the minimum and maximum shear stress values, a post processor which supports contourplots of the torsional shear stress on the cross section using the linear beam (CBAR) element forcesmust be used. The cross section location can be anywhere except the free end of the beam.
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 122.
Thermal Strain, Displacement, and Stress on Heated Beam
A beam originally 1 meter long and at –50° C is heated to 25° C. First, determine the displacementand thermal strain on a cantilever beam. Fix the beam at the free end and then determine thedisplacement, reaction forces, and stresses along the beam. Next, fix the beam at both ends.
Test Case Data and Information
Input Files
mstvl007.dat
Units
SI - meter
Model Geometry
Length = 1 m
Cross Sectional Properties
• Area = 0.01 m2
NX Nastran 11 Verification Manual 2-11
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Material Properties
• E = 2.068E11 Pa
• Coefficient of thermal expansion = 1.2E–05
• v = 0.3
Finite Element Modeling
• Create 10 linear beam (CBAR) elements on the X axis and restrain the end grids in all directions.
• Apply a temperature on all grid points.
Boundary Conditions
• Restraints
o Case 1: Restrain one end of the beam in all six directions.
o Case 2: Restrain both ends of the beam in all six directions.
• Loads
o Set grid temperatures to 25°C. Set the reference temperature to –50°C.
Solution Type
SOL 101 — Linear Statics
Results
Case 1
Result Bench Value NX NastranX Displacement at grid 11 (m) .0009000 .0009000Axial Thermal Strain .0009000 .0009000
Case 2
Result Bench Value NX NastranX Displacement (m) 0 0Axial Stress (Pa) 1.860E8 1.861E8X Reaction Force (N) 1.860E6 1.861E6
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 65.
2-12 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Uniformly Distributed Load on Linear Beam
A beam 40 feet long is restrained and loaded as shown with a distributed load of 10,000 lb/ft.Determine the bending stress and the deflection at the middle of the beam.
Test Case Data and Information
Input Files
mstvl008.dat
Units
Inch
Model Geometry
Length = 480 in.
NX Nastran 11 Verification Manual 2-13
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Cross Sectional Properties
• Rectangular cross section (1.17 in. x 43.24 in.)
• Iz = 7892 in.4
Material Properties
• E = 30E06 psi
Finite Element Modeling
Create 4 successive linear beam (CBAR) elements that are each 10 feet long.
Boundary Conditions
• Restraints
o Restrain the second and the fourth grids in five degrees of freedom. Do not restrain rotationabout Z.
• Loads
o Define a distributed load (force per unit length) of –10,000 lb/foot (global negative Ydirection) on the end elements.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranY Displacement at grid 3 (in.) 0.1820 0.182Max bending stress (psi) 1.644E4 1.644E4
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 98.
Membrane Loads on a Linear Quadrilateral Thin Shell Element
A circle is scribed on an unstressed aluminum plate. Forces acting in the plane of the plate causenormal stresses. Determine the change in the length of diameter AB and of diameter CD.
2-14 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Element Types
cquad4
Input Files
mstvl009.dat
Units
Inch
Model Geometry
• Length = 15 in.
• Diameter = 9 in.
• Thickness = 3/4 in.
NX Nastran 11 Verification Manual 2-15
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Material Properties
• E = 10E06 psi
• Poisson's ratio = 1/3
• F(x)/L = 9,000 lb/in.
• F(z)/L = 15,000 lb/in.
Finite Element Modeling
Create 1/4 of the model and apply symmetry boundary conditions. Then multiply the answer by 2 forcorrect results. Remember to account for the ratio of the circle diameter to plate length.
Boundary Conditions
• Restraints
o Restrain the left end of the beam in all six degrees.
• Loads
o Set the edge pressure to 9,000 lb/in. in the X direction and 15,000 lb/in. in the Z direction.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranX Diameter Change (in.) 4.800E-3 4.800E-3Z Diameter Change (in.) 14.40E-3 14.40E-3
Post Processing
• (dx at grid point 7 – dx at grid point 10) x 2 = (0.004 – 0.0016) x 2 = 0.0048
• (dz at grid point 7 – dz at grid point 24) x 2 = (0.012 –0.0048) x 2 = 0.0144
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 85.
Axial Loading on Rod Element
Determine the stress, elongation, and strain due to an axial load on a rod element.
2-16 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl011.dat
Units
SI - meters
Model Geometry
Length = 10 m
Cross Sectional Properties
• Area = 0.01 m2
Material Properties
• E = 200.0 GPa
Finite Element Modeling
Create a rod (CROD) element along the X axis.
Boundary Conditions
• Restraints
o Restrain an end of the rod in the 3 translational degrees.
• Loads
o Apply a grid point force in the positive X-direction of 500 kN.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranAxial Stress (MPa) 50.00 50.00Axial Strain 0.0002500 0.0002500Elongation (mm) 2.500 2.500
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 716.
NX Nastran 11 Verification Manual 2-17
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Stress on a Beam as It Expands and Closes a Gap
Determine the stress on a beam as it expands thermally and closes a 0.002 inch gap. It is initially at70 °F and is heated to 170 °F.
Test Case Data and Information
Input Files
mstvl013.dat
Units
Inch
Model Geometry
Length = 3 in.
Material Properties
• E = 1.05E07 psi
• Coefficient of thermal expansion = 1.25E–05 in./(in.–°F)
Finite Element Modeling
• Create a single linear beam (CBAR) element on the X axis.
2-18 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
• Create an MPC to define the closing of the gap.
Boundary Conditions
• Restraints
o Restrain the free end of the beam in all six degrees.
• Loads
o Set grid temperature to 170 °F.
o Set the reference temperature to 70 °F.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranAxial Stress (psi) –6.125E3 –6.125E3
References
Harris, C. O. Introduction to Stress Analysis 1959. p. 58.
Thin Wall Cylinder in Pure Tension
Determine the stress and deflection of a thin wall cylinder with a uniform axial load.
NX Nastran 11 Verification Manual 2-19
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl014.dat
Units
Inch
Model Geometry
• R = 0.5 in.
• Thickness = 0.01 in.
• y = 1.0 in.
Material Properties
• E = 10,000 psi
2-20 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
• ν = 0.3
Finite Element Modeling
Create 1/4 model of the cylinder with thin shell linear quadrilateral (CQUAD4) elements and symmetryboundary conditions.
Boundary Conditions
• Restraints
o Restrain edges of symmetry, in translation, in hoop direction, and rotation about Z axis.
o Restrain one end in Y direction.
Loads
o Apply membrane edge pressure of p / (pi)D = 3.1831 where p = 10 psi
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranAxial (Z) Stress (psi) 1.000E3 1.000E3Axial (Z) Deflection (in.) 0.100 0.100Radial Deflection (in.) –0.01500 –0.01500
References
Roark, R. and Young, W. Formulas for Stress and Strain, 6th Edition. New York: McGraw-Hill BookCompany, 1989. p. 518, Case 1a.
Thin-walled Cantilever Beam in Bending
Determine the maximum stress, maximum deflection, and strain energy for a thin-walled cantileverbeam subjected to a bending load.
NX Nastran 11 Verification Manual 2-21
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl015.dat
Units
Inch
Model Geometry
• Length = 30 in.
• Width = 5 in.
• Thickness = 0.1 in.
Material Properties
• E = 30E06 psi
• ν = 0.03
2-22 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
Finite Element Modeling
Create a 30 in. x 5 in. plate with thing shell (CQUAD4) elements.
Boundary Conditions
• Restraints
o Restrain at one of the ends in all directions.
• Loads
o Apply edge pressure of p/w = 1.2 lbs/in. where p = 6.0 lb.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranMax Deflection (in.) 4.320 4.264Max Bending Stress (psi) 2.160E4 1.980E4Total Strain Energy (lb in.) 12.96 12.79
References
Shigley, J. and Mitchel L. Mechanical Engineering Design, 4th Edition. New York: McGraw-Hill,Inc., 1983. pg. 804.
Strain Energy of a Truss
Determine the strain energy of a truss. The cross-sectional area of the diagonal members is twicethe cross-sectional area of the horizontal and vertical members.
NX Nastran 11 Verification Manual 2-23
Linear Statics Verification Using Theoretical Solutions
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Test Case Data and Information
Input Files
mstvl016.dat
Units
Inch
Model Geometry
• Length = 10 in.
Cross Sectional Properties
• Cross-sectional area (A) = 0.01 in.2
Material Properties
• E = 30E06 psi
Finite Element Modeling
Create truss shown using rod (CROD) elements.
Boundary Conditions
• Restraints
o Restrain far left grid in directions: X, Y, Z, RX, RY.
o Restrain far right grid in directions: Y, Z, RX, RY.
• Loads
2-24 NX Nastran 11 Verification Manual
Chapter 2: Linear Statics Verification Using Theoretical Solutions
Linear Statics Verification Using Theoretical Solutions
o Apply grid force in Y direction on lower center grid; F= 300 lb.
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX Nastran
Total Strain Energy (lb in.) 5.846 5.846
References
Beer and Johnston. Mechanics of Materials. New York: McGraw-Hill, Inc., 1992. p. 588.
NX Nastran 11 Verification Manual 2-25
Linear Statics Verification Using Theoretical Solutions
Chapter 3: Linear Statics Verification Using StandardNAFEMS Benchmarks
3.1 Overview of Linear Statics Verification Using Standard NAFEMSBenchmarksThe purpose of these linear statics test cases is to verify the function of NX Nastran using standardbenchmarks published by NAFEMS (National Agency for Finite Element Methods and Standards,National Engineering Laboratory, Glasgow, U.K.).
These standard benchmark tests were created by NAFEMS to stretch the limits of the finite elementsin commercial software. All results obtained using NX Nastran compare favorably with othercommercial finite element analysis software.
Understanding the Test Case Format
Each test case is structured with the following information:
• Test case data and information
o Physical and material properties
o Finite element modeling (modeling procedure or hints)
o Units
o Finite element modeling information
o Boundary conditions (loads and restraints)
o Solution type
• Results
• Reference
Reference
The following reference has been used in these test cases:
NAFEMS Finite Element Methods & Standards, The Standard NAFEMS Benchmarks. Glasgow:NAFEMS, Rev. 3, 1990.
NX Nastran 11 Verification Manual 3-1
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Test Cases
Elliptic Membrane
This test is a linear elastic analysis of an elliptic membrane (shown below) using coarse and finemeshes of plane stress elements and thin shell elements. It provides the input data and resultsfor NAFEMS Standard Benchmark Test LE1.
Ellipses:
Test Case Data and Information
Input Files
le101.dat (plane stress quadrilateral)
le102.dat (plane stress triangle)
le103.dat (thin shell)
Physical and Material Properties
• Thickness = 0.1 m
• Isotropic material
• E = 210E3 MPa
• v = 0.3
Units
SI
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
• Plane stress (only MID1 defined on PSHELL) linear (CQUAD4) and parabolic (CQUAD8)quadrilaterals — coarse and fine mesh.
• Plane stress (only MID1 defined on PSHELL) linear (CTRI3) and parabolic (CTRI6) triangles— coarse and fine mesh.
• Thin shell (MID1, MID2 and MID3 defined on PSHELL) linear (CQUAD4) and parabolic(CQUAD8) quadrilaterals — coarse and fine mesh.
• The fine mesh is created by approximately halving the coarse mesh.
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Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• Uniform outward pressure at outer edge BC = 10 MPa
• Inner curved edge AD unloaded
• X displacement (edge AB) = 0
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
• Y displacement (edge CD) = 0
Solution Type
SOL 101 — Linear Statics
Results
Output — tangential edge stress at D (stress in Y direction)
Plane Stress Elements
Test case Grid point # Bench Value NX NastranLinear quad — coarse mesh 4 92.7 62.1Linear quad — fine mesh 204 92.7 79.6
Parabolic quad — coarse mesh 104 92.7 82.1Parabolic quad — fine mesh 304 92.7 89.9Linear triangle — coarse mesh 4 92.7 52.9Linear triangle — fine mesh 204 92.7 70.8Parabolic triangle — coarse mesh 104 92.7 76.8Parabolic triangle — fine mesh 304 92.7 93.6
Thin Shell Elements
Test case Grid point # Bench Value NX NastranLinear quad — coarse mesh 4 92.7 62.1Linear quad — fine mesh 204 92.7 79.6Parabolic quad — coarse mesh 104 92.7 82.1Parabolic quad — fine mesh 304 92.7 89.9
NX Nastran 11 Verification Manual 3-5
Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
References
NAFEMS Finite Element Methods & Standards, The Standard NAFEMS Benchmarks, Test No. LE1.Glasgow: NAFEMS, Rev. 3, 1990.
Cylindrical Shell Patch Test
This test is a linear elastic analysis of a cylindrical shell (shown below) using thin shell elements andtwo different loadings. It provides the input data and results for NAFEMS Standard BenchmarkTest LE2.
Test Case Data and Information
Input Files
• le201a.dat (linear shell, case 1)
• le201b.dat (parabolic shell, case 1)
• le202a.dat (linear shell, case 2)
• le202b.dat (parabolic shell, case 2)
Physical and Material Properties
• Thickness = 0.1 m
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
• Isotropic material
• E = 210E3 MPa
• v = 0.3
Units
SI
Finite Element Modeling
• Thin shell linear (CQUAD4) and parabolic (CQUAD8) quadrilaterals
Boundary Conditions
• Translations and rotations (edge AB) = 0
• Z translations and normal rotations (edge AD and edge BC) = 0
Case 1 loading:
• Uniform normal edge moment on DC = 1.0 kNm/m
Case 2 loading:
• Uniform outward normal pressure at mid-surface ABCD = 0.6 MPa
• Tangential outward normal pressure on edge DC = 60.0 MPa
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Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 101 — Linear Statics
Results
Output — outer (convex) surface (top shell surface) tangential stress at point E (grid point 2):
Test case Filename Bench Value NX NastranLinear quad – case 1 le201a 60.00 51.8Linear quad – case 2 le202a 60.00 51.1*Parabolic quad – case 1 le201b 60.00 56.4Parabolic quad – case 2 le202b 60.00 56.4** Since the shapes of the shells are an approximation to a cylindrical surface, an edge load willnot be in the correct direction. To get this result, the edge load must be input as grid forces in thetangential direction.
Post Processing
• Stress component: Y
• Results obtained on the element top surface in cylindrical coordinate system
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
References
NAFEMS Finite Element Methods & Standards, The Standard NAFEMS Benchmarks, Test No. LE2.Glasgow: NAFEMS, Rev. 3, 1990.
Hemisphere-Point Loads
This test is a linear elastic analysis of hemisphere point loads (shown below) using coarse andfine meshes of thin shell elements. It provides the input data and results for NAFEMS StandardBenchmark Test LE3.
Test Case Data and Information
Input Files
• le301.dat (linear quad, coarse mesh)
• le302.dat (linear quad, fine mesh)
• le303.dat (parabolic quad, coarse mesh)
Physical and Material Properties
• Thickness = 0.04 m
• Isotropic material
• E = 68.25 × 103 MPa
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Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
• v = 0.3
Units
SI
Finite Element Modeling
• Thin shell linear (CQUAD4) and parabolic (CQUAD8) quadrilaterals — coarse and fine mesh
• Equally spaced grid points on AC, CE, EA
• Point G at X = Y = Z = 10 /( 31/2) grid point 7
Boundary Conditions
• Edge AE symmetry about XZ plane (y = rotation x = rotation z = 0)
• Edge CE symmetry about YZ plane (x = rotation y = rotation z = 0)
• Point E (x = y = z = 0)
• All other displacements on edge AC are free.
• Concentrated radial load outward at A = 2KN
• Concentrated radial load inward at C = 2KN
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 101 — Linear Statics
Results
Output — X displacement at point A
Mesh Test Case Bench Value NX Nastranlinear quad — coarse mesh le301 0.185 0.1848linear quad — fine mesh le302 0.185 0.1865parabolic quad — coarse mesh le303 0.185 0.1416
References
NAFEMS Finite Element Methods & Standards, The Standard NAFEMS Benchmarks, Test No. LE3.Glasgow: NAFEMS, Rev. 3, 1990.
Z-Section Cantilever
This test is a linear elastic analysis of a Z-section cantilever (shown below) using thin shell elements.It provides the input data and results for NAFEMS Standard Benchmark Test LE5.
NX Nastran 11 Verification Manual 3-11
Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
• le501.dat (linear quadrilateral)
• le502.dat (parabolic quadrilateral)
Physical and Material Properties
• Thickness = 0.1 m
• Isotropic material
• E = 210E3 MPa
• v = 0.3
Units
SI
Finite Element Modeling
• Thin shell linear (CQUAD4) and parabolic (CQUAD8) quadrilaterals
Boundary Conditions
• All displacements on edges B1, B2, B3 = 0
• Torque of 1.2MN applied at end C by two edge shears (at C1 & C3) of 0.6 MN
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 101 — Linear Statics
Results
Output — averaged axial stress at mid-surface, point A, grid point 30 (compression)
Result Bench Value NX NastranLinear quad - point A/grid point 30 –108.0 –111.0Parabolic quad - point A/grid point 30 –108.0 –110.3
References
NAFEMS Finite Element Methods & Standards. The Standard NAFEMS Benchmarks, Test No. LE5.Glasgow: NAFEMS, Rev. 3, 1990.
Skew Plate Normal Pressure
This test is a linear elastic analysis of a plate (shown below) using thin shell elements. It provides theinput data and results for NAFEMS Standard Benchmark Test LE6.
Test Case Data and Information
Input Files
• le601.dat (linear and parabolic quad)
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Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
• le602.dat (linear and parabolic triangle)
Physical and Material Properties
• Thickness = 0.01 m
• Isotropic material
• E = 210E3 MPa
• v = 0.3
Units
SI
Finite Element Modeling
• Thin shelllinear (CQUAD4) and parabolic (CQUAD8) quadrilaterals — coarse and fine mesh
• Thin shell linear (CTRI3) and parabolic (CTRI6) triangles — coarse and fine mesh
Boundary Conditions
• Simple supports
• Z displacement = 0
• Normal pressure = –0.7KPa in the Z direction
Solution Type
SOL 101 — Linear Statics
Results
Output — maximum principal stress on the bottom surface at the plate center.
Case le601
Mesh Grid point # Bench Value NX NastranLinear quad coarse mesh 9 0.802 0.325Linear quad fine mesh 18 0.802 0.683Parabolic quad coarse mesh 43 0.802 0.625
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Mesh Grid point # Bench Value NX NastranParabolic quad fine mesh 52 0.802 0.719
Case le602
Mresh Grid point # Bench Value NX NastranLinear triangle coarse mesh 9 0.802 0.396Linear triangle fine mesh 18 0.802 0.720Parabolic triangle coarse mesh 43 0.802 0.926Parabolic triangle fine mesh 52 0.802 0.857
References
NAFEMS Finite Element Methods & Standards. The Standard NAFEMS Benchmarks, Test No. LE6.Glasgow: NAFEMS, Rev. 3, 1990.
Thick Plate Pressure
This article provides the input data and results for NAFEMS Standard Benchmark Test LE10. This testis a linear elastic analysis of a thick (shown below) using coarse and fine meshes of solid elements.
Ellipses:
Test Case Data and Information
Input Files
• le1001.dat (linear and parabolic brick)
• le1002.dat (linear and parabolic wedge)
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
• le1003.dat (linear and parabolic tetrahedron)
• le1004.dat (linear and parabolic pyramid)
Physical and Material Properties
• Isotropic material
• E = 210E3 MPa
• v = 0.3
Units
SI
Finite Element Modeling
• Solid brick (CHEXA) linear and parabolic - coarse and fine mesh
• Solid wedge (CPENTA) linear and parabolic - coarse and fine mesh
• Solid tetrahedron (CTETRA) - linear and parabolic - coarse and fine mesh
• Solid pyramid (CPYRAM) linear and parabolic - coarse and fine mesh (created by dividing eachlinear and parabolic brick element into 6 pyramid elements)
Solid Brick
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Solid Wedge
Solid Tetrahedron — fine mesh only
Boundary Conditions
• Uniform normal pressure on the upper surface of the plate = 1 MPa
• Inner curved edge AD unloaded
• X and Y displacements on faces DCD'C′ and ABA′B′ = 0
• X and Y displacements on face BCB′C′ are fixed
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
• Z displacements along mid-plane are fixed
Solution Type
SOL 101 — Linear Statics
Results
Output — direct stress at point Dσyy
Test Case le1001
Mesh Grid point # Bench Value NX NastranLinear brick — coarse mesh 4 –5.50 –5.41Linear brick — fine mesh 204 –5.50 –5.67Parabolic brick — coarse mesh 104 –5.50 –6.13Parabolic brick — fine mesh 304 –5.50 –6.04
Test Case le1002
Mesh Grid point # Bench Value NX NastranLinear wedge — coarse mesh 4 –5.50 –5.94Linear wedge — fine mesh 204 –5.50 –5.83Parabolic wedge — coarse mesh 104 –5.50 –5.32Parabolic wedge — fine mesh 304 –5.50 –6.01
Test Case le1003
Result Grid point # Bench Value NX NastranLinear tetra — fine mesh 40 –5.50 –2.41Parabolic tetra — fine mesh 171 –5.50 –5.28
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Test Case le1004
Mesh Grid point # Bench Value NX NastranLinear pyramid — coarse mesh 4 –5.50 –2.85Linear pyramid — fine mesh 204 –5.50 –3.83Parabolic pyramid — coarsemesh
104 –5.50 –5.60
Parabolic pyramid — fine mesh 304 –5.50 –5.72
References
NAFEMS Finite Element Methods & Standards. The Standard NAFEMS Benchmarks, Test No. LE10.Glasgow: NAFEMS, Rev. 3, 1990.
Solid Cylinder/Taper/Sphere — Temperature
This test is a linear elastic analysis of a solid cylinder with a temperature gradient (shown below)using coarse and fine meshes of solid elements. It provides the input data and results for NAFEMSStandard Benchmark Test LE11.
Test Case Data and Information
Input Files
• le1101a.dat (linear brick — coarse mesh)
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
• le1101b.dat (linear brick — fine mesh)
• le1102a.dat (parabolic brick — coarse mesh)
• le1102b.dat (parabolic brick — fine mesh)
• le1103a.dat (linear wedge — coarse mesh)
• le1103b.dat (linear wedge — fine mesh)
• le1104a.dat (parabolic wedge — coarse mesh)
• le1104b.dat (parabolic wedge — fine mesh)
• le1105a.dat (linear tetra — coarse mesh)
• le1105b.dat (linear tetra — fine mesh)
• le1106a.dat (parabolic tetra — coarse mesh)
• le1106b.dat (parabolic tetra — fine mesh)
• le1107a.dat (linear pyramid — coarse mesh)
• le1107b.dat (linear pyramid — fine mesh)
• le1108a.dat (parabolic pyramid — coarse mesh)
• le1108b.dat (parabolic pyramid — fine mesh)
Physical and Material Properties
• Isotropic material
• E = 210E3 MPa
• v = 0.3
• a = 2.3E–4 °C
Units
SI
Finite Element Modeling
• Solid brick (CHEXA) linear and parabolic — coarse and fine mesh
• Solid wedge (CPENTA) linear (6 grid point) and parabolic (15 grid point) — coarse and fine mesh
• Solid tetrahedron (CTETRA) linear and parabolic — coarse and fine mesh
• Solid pyramid (CPYRAM) linear and parabolic — coarse and fine mesh (created by dividing eachlinear and parabolic brick element into 6 pyramid elements)
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Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Linear Statics Verification Using Standard NAFEMS Benchmarks
Solid Brick
Solid Tetrahedron
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Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 3: Linear Statics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• Linear temperature gradient in the radial and axial direction
T° C = (X2 + Y2)1/2 + Z
• X, Y, and Z displacements = 0
• X and Y displacements on face BCB′C′ are fixed
• Z displacements on XY-plane face and HIH′I′ face = 0
Solution Type
SOL 101 — Linear Statics
Results
Output - direct stress σyy at point A
File Name Result Grid point atPoint A
BenchValue
NXNastran
le1101a Linear brick — coarse mesh 30 –105.0 –88.50le1101b Linear brick — fine mesh 71 –105.0 –98.3le1102a Parabolic brick — coarse mesh 67 –105.0 –100.4le1102b Parabolic brick — fine mesh 159 –105.0 –111.2le1103a Linear wedge — coarse mesh 33 –105.0 –10.0le1103b Linear wedge — fine mesh 74 –105.0 –48.3le1104a Parabolic wedge — coarse mesh 71 –105.0 –87.2le1104b Parabolic wedge — fine mesh 187 –105.0 –96.2le1105a Linear tetra — coarse mesh 8 –105.0 –31.4
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Linear Statics Verification Using Standard NAFEMS Benchmarks
File Name Result Grid point atPoint A
BenchValue
NXNastran
le1105b Linear tetra — fine mesh 8 –105.0 –65.2le1106a Parabolic tetra — coarse mesh 8 –105.0 –89.6le1106b Parabolic tetra — fine mesh 8 –105.0 –97.3le1107a Linear pyramid — coarse mesh 30 –105.0 –57.0le1107b Linear pyramid — fine mesh 71 –105.0 –79.8le1108a Parabolic pyramid — coarse mesh 67 –105.0 –65.8le1108b Parabolic pyramid — fine mesh 159 –105.0 –108.8
References
NAFEMS Finite Element Methods & Standards. The Standard NAFEMS Benchmarks, Test No. LE11.Glasgow: NAFEMS, Rev. 3, 1990.
NX Nastran 11 Verification Manual 3-23
Linear Statics Verification Using Standard NAFEMS Benchmarks
Chapter 4: Normal Mode Dynamics Verification
4.1 Overview of Normal Mode Dynamics Verification UsingTheoretical SolutionsThe purpose of these normal mode dynamics test cases is to verify the function of NX Nastran usingtheoretical solutions. The test cases are relatively simple in form and most of them have closed-formtheoretical solutions.
The theoretical solutions shown in these examples are from well known engineering texts. For eachtest case, a specific reference is cited. All theoretical reference texts are listed at the end of this topic.
The finite element method is very flexible in the types of physical problems represented. Theverification tests provided are not exhaustive in exploring all possible problems, but representcommon types of applications.
This overview provides information on the following:
• Understanding the test case format
• Understanding comparisons with theoretical solutions
• References
Understanding the Test Case Format
Each test case is structured with the following information.
• Test case data and information:
o Physical and material properties
o Finite element modeling (modeling procedure or hints)
o Units
o Solution type
o Boundary conditions (loads and restraints/constraints)
• Results
• Reference
Understanding Comparisons with Theoretical Solutions
While differences in finite element and theoretical results are, in most cases, negligible, some testswould require an infinite number of elements to achieve the exact solution. Elements are chosen toachieve reasonable engineering accuracy with reasonable computing times.
NX Nastran 11 Verification Manual 4-1
Chapter 4: Normal Mode Dynamics Verification
Results reported here are results which you can compare to the referenced theoretical solution.Other results available from the analyses are not reported here. Results for both theoretical and finiteelement solutions are carried out with the same significant digits of accuracy.
The closed-form theoretical solution may have restrictions, such as rigid connections, that do notexist in the real world. These limiting restrictions are not necessary for the finite element model, butare used for comparison purposes. Verification to real world problems is more difficult but should bedone when possible.
The actual results from NX Nastran may vary insignificantly from the results presented in thisdocument. This variation is due to different methods of performing real numerical arithmetic ondifferent systems. In addition, it is due to changes in element formulations which have been made toimprove results under certain circumstances.
Reference
The following references have been used in the normal mode dynamics analysis verificationproblems presented:
1. Blevins, R. Formulas For Natural Frequency and Mode Shape, 1st Edition. New York: VanNorstrand Reinhold Company, 1979.
2. Timoshenko and Young. Vibration Problems in Engineering. New York: Van Norstrand ReinholdCompany, 1955.
3. Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, Theory and Applications. Boston: Allynand Bacon, Inc., 1978.
4. Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, 2nd Edition. Boston: Allyn and Bacon,Inc., 1978.
Test Cases
Undamped Free Vibration — Single Degree of Freedom
Determine the natural frequency of the system shown.
4-2 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
Test Case Data and Information
Input File
mstvn002.dat
Units
SI - meter
Model Geometry
• Length = 0.5 m
• a = 0.3 m
Physical Properties
• mass = 20 Kg
• k = 8 KN/m
Finite Element Modeling
• Create 5 rigid bar (RBAR) elements along the X axis. Each bar should be 0.1 m long.
• A lumped mass (CONM2) element is applied on the end grid point.
NX Nastran 11 Verification Manual 4-3
Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
• A grid point-to-ground spring element (CELAS1) is applied 0.2 m from the lumped mass.
Boundary Conditions
• Restrain the first grid point to allow rotation only in the Z direction.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results
Result Bench Value NX NastranFrequency (Hz) 1.910 1.910
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, Theory and Applications, p. 75. Boston:Allyn and Bacon, Inc., 1978.
Two Degrees of Freedom Undamped Free Vibration — Principle Modes
Determine the natural frequencies of a dynamic system with two degrees of freedom.
4-4 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
Test Case Data and Information
Input File
mstvn003.dat
Units
SI- meter
Element Types
• Translational springs (CELAS1)
• Lumped mass (CONM2)
NX Nastran 11 Verification Manual 4-5
Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
Physical Properties
• Mass = 1 kg
• k = 1 N/m
Finite Element Modeling
• Create four grid points on the Y axis.
• Create three linear springs (CELAS1) with stiffness of 1 N/m and with a uniaxial stiffnessreference coordinate system.
• Create two lumped mass elements (CONM2) with a mass of 1 kg.
Boundary Conditions
• Restrain ends in all directions.
• Restrain other grid points in all directions but Y.
Solution Type
Normal Mode Dynamics - SOL 103, Lanczos method
Results
Result Bench Value NX NastranFrequency of Mode 1 (Hz) 0.1592 0.1592Frequency of Mode 2 (Hz) 0.2757 0.2757
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, 2nd Edition, pp. 145-149. Boston: Allynand Bacon, Inc., 1978.
Three Degrees of Freedom Torsional System
Determine the natural frequencies of a dynamic system with three degrees of freedom.
4-6 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
Test Case Data and Information
Input File
mstvn004.dat
Element Types
• Rotational springs (CELAS1)
• Lumped mass (CONM2)
Units
SI — meter
Physical Properties
• J = J1 = J2 = J3 = 0.1
• k = k1 = k2 = k3 = 1 N*m
Finite Element Modeling
• Create four grid points on the X axis.
• Create three linear torsional springs (CELAS1) with stiffness of 1 N*m and with a stiffnessreference coordinate system being uniaxial.
• Create three lumped mass elements (CONM2) with a mass coordinate system = 1 and with massinertia system of: 0.1, 0.0, 0.0, 0.0, 0.0, 0.0.
Boundary Conditions
• Restrain one end in all directions.
• Restrain the other grid points in all directions but RX.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos method
Results
Result Bench Value NX NastranFrequency of Mode 1 (Hz) 0.2240 0.2240Frequency of Mode 2 (Hz) 0.6276 0.6276Frequency of Mode 3 (Hz) 0.9069 0.9069
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, 2nd Edition, pp. 153-155. Boston: Allynand Bacon, Inc., 1978.
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Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
Two Degrees of Freedom Vehicle Suspension System
Determine the natural frequencies of dynamic system with two degrees of freedom. Degrees offreedom are one translational and one rotational.
Test Case Data and Information
Input Files
mstvn005.dat
Units
SI - meter
Physical Properties
• Mass = 1800 kg
• K1 = 42000 N/m
• K2 = 48000 N/m
Finite Element Modeling
• Create a linear translation spring (CELAS1) with stiffness of K1
• Create a linear translation spring (CELAS1) with stiffness of K2
• Create a lumped mass element (CONM2) with a mass coordinate system = 1 and mass inertiasystem of: 0.0, 0.0, 3528, 0.0, 0.0, 0.0.
4-8 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
• Create a three-noded rigid element (RBE2)
Boundary Conditions
• Nodal displacement restraints
o Restrain grid points 4 and 5 in all directions.
o Restrain the other grid points in all directions but Y and RZ.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results
Result Bench Value NX NastranFrequency of Mode 1 (Hz) 1.086 1.086Frequency of Mode 2(Hz) 1.496 1.496
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations. Boston: Allyn and Bacon, Inc., 1978. pp.150-153.
Two Degrees of Freedom Vehicle Suspension System
Determine the natural frequencies of dynamic system with two degrees of freedom. Degrees offreedom are one translational and one rotational.
NX Nastran 11 Verification Manual 4-9
Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
Test Case Data and Information
Input File
mstvn005.dat
Element Types
• Translational springs (CELAS1)
• Lumped mass (CONM2)
• Rigid (RBE2)
Units
SI — meter
Model Geometry
• Length1 = 1.6 m
• Length2 = 2.0 m
• r = 1.4 m (gyration radius; J = m*r*r)
Physical Properties
• mass = 1800 kg
• K1 = 42000 N/m
• K2 = 48000 N/m
Finite Element Modeling
• Create five grid points in the XY plane with the following coordinates:
o Grid point 1 = (0,0)
o Grid point 2 = (12,0)
o Grid point 3 = (–L1,0)
o Grid point 4 = (L2,–1)
o Grid point 5 = (–L1,–1)
• Create a linear translation spring (CELAS1) with stiffness of K1 between grid point 1 and gridpoint 5.
• Create a linear translation spring (CELAS1) with stiffness of K2 between grid point 2 and gridpoint 4.
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Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
• Create a lumped mass element (CONM2) with a mass coordinate system = 1 and mass inertiasystem of: 0.0, 0.0, 3528, 0.0, 0.0, 0.0.
• Create a three-grid-point rigid element (RBE2) using grid point 1, grid point 2, and grid point 3.
Boundary Conditions
• Restrain grid points 4 and 5 in all directions.
• Restrain the other grid points in all directions but Y and RZ.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results
Result Bench Value NX NastranFrequency of Mode 1 (Hz) 1.086 1.086Frequency of Mode 2(Hz) 1.496 1.496
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, pp. 150-153. Boston: Allyn and Bacon,Inc., 1978.
Cantilever Beam Undamped Free Vibrations
Determine the natural frequencies of a cantilever beam.
Test Case Data and Information
Input File
mstvn006.dat
Element Type
Linear beam (CBEAM)
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Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
Units
Inch
Model Geometry
• Length = 100 in.
• Height = 2 in.
Physical and Material Properties
• w = 1 lb/in.
• J = .10
• Poisson's ratio = .3
Calculated Data
• A = h2 = 4 in2
• I = h4/12 = 1.33333
• G = E/2 × 1/1 + nu = 11538461.54
• m = w/g = 2.59067375E–3
• Ip = Ixx + Iyy = 2.66666
Finite Element Modeling
• Create 11 grid points on X axis.
• Create 10 linear beams (CBEAM) between grid points.
Boundary Conditions
• Restrain one end grid point in all directions.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results
Result Bench Value NX NastranFrequency of Modes 1 & 2 (TransverseVibration)
6.953 6.953
Frequency of Modes 3 & 4 (TransverseVibration)
43.58 43.58
Frequency of Mode 5 (Torsional Vibration) 64.68 64.68
4-12 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Normal Mode Dynamics Verification
Result Bench Value NX NastranFrequency of Modes 6 & 7 (TransverseVibration)
122.0 122.0
Frequency of Mode 8 (Torsional Vibration) 193.9 195.7Frequency of Modes 9 & 10 (TransverseVibration)
238.8 239.3
References
Blevins, R. Formulas For Natural Frequency and Mode Shape, 1st Edition, pp. 108,193. New York:Van Norstrand Reinhold Company, 1979.
Natural Frequency of a Cantilevered Mass
Determine the natural frequencies of a dynamic system consisting of a massless beam and a lumpedmass at the end.
Test Case Data and Information
Input File
mstvn007.dat
Element Types
• Linear beam (CBAR)
• Lumped mass (CONM2)
Units
Inch
Model Geometry
Length = 30 in.
Physical and Material Properties
• Mass = 0.5 lbm
NX Nastran 11 Verification Manual 4-13
Normal Mode Dynamics Verification
Chapter 4: Normal Mode Dynamics Verification
• E = 30E6 psi
• Density = 1.0E–6
• I = 1.5 in.4
Finite Element Modeling
• Create 2 grid points on the X axis with coordinates (0,0,0) and (30,0,0).
• Create a linear beam (CBAR) element between grid points with shear area ratio = 0.
• Create a lumped mass (CONM2) on one grid point with mass of 0.5 lbm.
Boundary Conditions
• Restrain wall end in all directions.
• Restrain mass end in directions of Z, RX, and RY.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos method
Results
Result Bench Value NX NastranMode 2 Frequency (Hz) 15.92 15.92
References
Tse, F., Morse, I., and Hinkle, R. Mechanical Vibrations, 2nd Edition, p. 72. Boston: Allyn and Bacon,Inc., 1978.
4-14 NX Nastran 11 Verification Manual
Chapter 4: Normal Mode Dynamics Verification
Chapter 5: Normal Mode Dynamics Verification UsingStandard NAFEMS Benchmarks
5.1 Overview of Normal Mode Dynamics Verification Using StandardNAFEMS BenchmarksThe purpose of these normal mode dynamics test cases is to verify the function of NX Nastranusing standard benchmarks published by NAFEMS (National Agency for Finite Element Methodsand Standards, National Engineering Laboratory, Glasgow, U.K.).
These standard benchmark tests were created by NAFEMS to stretch the limits of the finite elementsin commercial software. All results obtained using NX Nastran compare favorably with othercommercial finite element analysis software. Results of these test cases using other commercial finiteelement analysis software programs are available from NAFEMS.
Understanding the Test Case Format
Each test case is structured with the following information.
• Test case data and information:
o Units
o Physical and material properties
o Finite element modeling information
o Boundary conditions (loads and restraints/constraints)
o Solution type
• Results
• Reference
Reference
The following reference has been used in these test cases:
NAFEMS Finite Element Methods & Standards. Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis. Glasgow: NAFEMS, Nov., 1987.
NX Nastran 11 Verification Manual 5-1
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Beam Element Test Cases
Pin-ended Cross — In-plane Vibration
This test is a normal mode dynamic analysis of a pin-ended cross (shown below) using beamelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 1.
Attributes of this test are:
• Coupling between flexural and extensional behavior
• Repeated and close eigenvalues
Test Case Data and Information
Input Files
• nf001ac.dat (linear consistent)
• nf001al.dat (linear lumped)
Units
SI
Cross Sectional Properties
• Area = .015625 m2
Shear ratio:
• Y = 0
5-2 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Z = 0
Material Properties
• E = 200E09 N/m2
• ρ=8000 kg/m3
• ν = 0.29 (Poisson's ratio)
• G = 8.01E10
Finite Element Modeling
• Four linear beam (CBAR) elements per arm
Boundary Conditions
• X = Y = 0 at A, B, C, D
• Z = Rx = Ry = 0 at all grid points
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (lumped mass on, param coupmass = –1)
• Using coupled mass (lumped mass off, param coupmass = 1)
NX Nastran 11 Verification Manual 5-3
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode ReferenceValue (Hz)
NAFEMS TargetValue (Hz)
NX Nastran Result(lumped mass) (Hz)
NX Nastran Result(coupled mass) (Hz)
1 11.34 11.34 11.33 11.342, 3 17.71 17.69 17.66 17.694 17.71 17.72 17.69 17.725 45.35 45.48 45.02 45.526, 7 57.39 57.36 56.06 57.438 57.39 57.68 56.34 57.75
References
NAFEMS Finite Element Methods & Standards. Abbassian, F., Dawswell, D. J., and Knowles, N.C.Selected Benchmarks for Natural Frequency Analysis Test No. 1. Glasgow: NAFEMS, Nov., 1987.
Pin-ended Double Cross - In-plane Vibration
This test is a normal mode dynamic analysis of a pin-ended double cross (shown below) using beamelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 2.
Attributes of this test are:
• Coupling between flexural and extensional behavior
• Repeated and close eigenvalues
5-4 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
• nf002ac.dat (linear consistent)
• nf002al.dat (linear lumped)
Units
SI
Cross Sectional Properties
Key-in section:
• Area = .015625 m2
Shear ratio:
• Y = 0
• Z = 0
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
Finite Element Modeling
• Four linear beam (CBAR) elements per arm
Boundary Conditions
• X = Y = 0 at A, B, C, D, E, F, G, H
• Z = Rx= Ry = 0 at all grid points
NX Nastran 11 Verification Manual 5-5
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (lumped mass toggle on, param coupmass = –1)
• Using coupled mass (lumped mass toggle off, param coupmass = 1)
Results
Mode ReferenceValue (Hz)
NAFEMS TargetValue (Hz)
NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
1 11.34 11.34 11.33 11.342, 3 17.71 17.69 17.66 17.694, 5, 6, 7,8 17.71 17.72 17.69 17.729 45.35 45.48 45.02 45.5210, 11 57.39 57.36 56.06 57.4312, 13, 14, 15,16
57.39 57.68 56.34 57.75
References
NAFEMS Finite Element Methods & Standards. Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 2. Glasgow: NAFEMS, Nov., 1987.
5-6 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Free Square Frame - In-plane Vibration
This test is a normal mode dynamic analysis of a free square frame (shown below) using beamelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 3.
Attributes of this test are:
• Coupling between flexural and extensional behavior
• Rigid body modes (3 modes)
• Repeated and close eigenvalues
Test Case Data and Information
Input Files
• nf003ac.dat (linear consistent)
• nf003al.dat (linear lumped)
Units
SI
Cross Sectional Properties
Shear ratio:
• Y = 1.0
• Z = 1.0
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
NX Nastran 11 Verification Manual 5-7
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
• Four linear beam (CBAR) elements per arm
Boundary Conditions
• Rotations fixed, translations free
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (lumped mass toggle on, param coupmass = –1)
• Using coupled mass (lumped mass toggle off, param coupmass = 1)
Results
Mode ReferenceValue (Hz)
NAFEMS TargetValue (Hz)
NX NastranResult (lumpedmass) (Hz)
NX Nastran Result(coupled mass) (Hz)
4 3.261 3.262 3.259 3.2595 5.668 5.665 5.660 5.6636, 7 11.14 11.15 10.89 11.138 12.85 12.83 12.74 12.809 24.57 24.66 23.53 24.6410, 11 28.70 28.81 28.13 28.73
References
NAFEMS Finite Element Methods & Standards. Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 3. Glasgow: NAFEMS, Nov., 1987.
5-8 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Cantilever with Off-center Point Masses
This test is a normal mode dynamic analysis of a cantilever with off-center point masses (shownbelow) using beam elements. This document provides the input data and results for NAFEMSSelected Benchmarks for Natural Frequency Analysis,Test 4.
Attributes of this test are:
• Coupling between torsional and flexural behavior
• Inertial axis non-coincident with flexibility axis
• Discrete lumped mass, rigid links
• Close eigenvalues
Test Case Data and Information
Input Files
• nf004a.dat
Units
SI
Cross Sectional Properties
Shear ratio:
• Y = 1.128
• Z = 1.128
Material Properties
• E = 200E09 N/m 2
• ρ = 8000 kg/m3
• ν = 0.3
NX Nastran 11 Verification Manual 5-9
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
• Five linear beam (CBAR) elements along cantilever
Boundary Conditions
• X = Y = Z = Rx = Ry = Rz = 0 at A
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos (Parameter COUPMASS = –1)
Results
Mode Reference Value(Hz)
NAFEMS Target Value(Hz)
NX Nastran Result (Hz)
1 1.723 1.723 1.7142 1.727 1.727 1.7203 7.413 7.413 7.5544 9.972 9.972 9.9545 18.16 18.16 17.686 26.96 26.97 26.78
References
NAFEMS Finite Element Methods & Standards. Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 4. Glasgow: NAFEMS, Nov., 1987.
Deep Simply-Supported Beam
This test is a normal mode dynamic analysis of a deep simply supported beam (shown below).This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 5.
5-10 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Shear deformation and rotary inertial (Timoshenko beam)
• Possibility of missing extensional modes when using iteration solution methods
• Repeated eigenvalues
Test Case Data and Information
Input Files
• nf005ac.dat (linear consistent, param coupmass = 1)
• nf005al.dat (linear lumped, param coupmass = –1)
Units
SI
Cross Sectional Properties
Shear ratio:
• Y = 1.176923
• Z = 1.176923
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
• Five linear beam elements (CBEAM)
Boundary Conditions
• X = Y = Z = Rx =0 at A
NX Nastran 11 Verification Manual 5-11
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Y = Z = 0 at B
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (lumped mass on, param coupmass = –1)
• Using coupled mass (lumped mass off, param coupmass = 1)
Results
Mode ReferenceValue (Hz)
NAFEMS TargetValue (Hz)
NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
1, 2 (flexural) 42.65 42.57 43.15 43.263 (torsional) 77.54 77.84 77.20 77.844 (extensional) 125.0 125.5 124.5 125.55, 6 (flexural) 148.3 145.5 149.8 154.97 (torsional) 233.1 241.2 224.1 241.28, 9 (flexural) 284.6 267.0 271.0 306.7
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 5. Glasgow: NAFEMS, Nov., 1987.
Circular Ring — In-plane and Out-of-plane Vibration
This test is a normal mode dynamic analysis of a circular ring (shown below) using beam elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 6.
5-12 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Rigid body modes (six modes)
• Repeated eigenvalues
Test Case Data and Information
Input Files
• nf006ac.dat (param coupmass = 1)
• nf006al.dat (param coupmass = –1)
Units
SI
Cross Sectional Properties
Shear ratio:
• Y = 1.128205
• Z = 1.128205
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
• 20 linear beam (CBAR) elements
NX Nastran 11 Verification Manual 5-13
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• X = Y = Z = Rx = Ry = Rz active
• Model is unsupported.
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained two different ways:
• Using coupled mass (param coupmass = –1)
• Using lumped mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
NAFEMS TargetValue (Hz)
NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
7, 8 (out ofplane)
51.85 52.29 51.62 52.38
9, 10 (in plane) 53.38 53.97 54.05 53.8011, 12 (out ofplane)
148.8 149.7 146.9 149.7
13, 14 (in plane) 151.0 152.4 152.2 151.515, 16 (out ofplane)
287.0 288.3 280.4 287.3
17, 18 (in plane) 289.5 288.3 289.2 289.1
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 6. Glasgow: NAFEMS, Nov., 1987.
Cantilevered Beam
This test is a normal mode dynamic analysis of a cantilevered beam (shown below). This documentprovides the input data and results for NAFEMS Selected Benchmarks for Natural FrequencyAnalysis, Test 71.
5-14 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Ill-conditioned stiffness matrix
Test Case Data and Information
Input Files
• nf071a.dat (Test 1)
• nf071b.dat (Test 2)
• nf071c.dat (Test 3)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ=8000 kg/m3
Finite Element Modeling
Three tests — all use linear beam (CBAR) elements
• Test 1: a = b
• Test 2: a = 10b
• Test3: a = 100b
Boundary Conditions
• X = Y = Rz = 0 at A
• Z = 0 at all grid points
• Rx = Ry = 0 at all grid points
NX Nastran 11 Verification Manual 5-15
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Beams always use a coupled mass formulation (param coupmass = 1).
Results
Mode Reference Value (Hz) Mesh NX Nastran Result (Hz)1 1.010 a = b
a = 10b
a = 100b
1.010
1.010
1.0102 6.327 a = b
a = 10b
a = 100b
6.324
6.327
6.3303 17.72 a = b
a = 10b
a = 100b
17.70
17.80
17.834 34.72 a = b
a = 10b
a = 100b
34.70
34.86
35.075 57.39 a = b
a = 10b
a = 100b
57.48
60.64
64.826 85.73 a = b
a = 10b
a = 100b
86.24
101.86
104.74
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis Test No. 71. Glasgow: NAFEMS, Nov., 1987.
Shell Element Test Cases
Thin Square Cantilevered Plate — Symmetric Modes
This test is a normal mode dynamic analysis of a thin, square, cantilevered plate meshed with NXNastran shell elements. This document provides the input data and results for NAFEMS SelectedBenchmarks for Natural Frequency Analysis, Test 11a.
5-16 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Symmetric modes, symmetric boundary conditions along the cutting plane
Test Case Data and Information
Input Files
• nf011a_l.dat (4-noded quadrilateral, lumped mass)
• nf011a_c.dat (4-noded quadrilateral, coupled mass)
• nf011ha_l.dat (8-noded quadrilateral, lumped mass)
• nf011ha_c.dat (8-noded quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 32 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.05m
• 8 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05m
NX Nastran 11 Verification Manual 5-17
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z = Ry = Rx = 0 along Y-axis
• Rx = 0 along Y = 5m
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NX NastranResult (lumpedmass)(Hz)
NX NastranResult (coupledmass(Hz)
1 0.4210 Linear
Parabolic
0.4150
0.4150
0.4180
0.4180
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode ReferenceValue (Hz)
Mesh NX NastranResult (lumpedmass)(Hz)
NX NastranResult (coupledmass(Hz)
2 2.582 Linear
Parabolic
2.490
2.478
2.604
2.5673 3.306 Linear
Parabolic
3.115
3.134
3.314
3.2714 6.555 Linear
Parabolic
6.044
6.163
6.538
6.5395 7.381 Linear
Parabolic
7.094
7.099
7.808
7.4956 11.40 Linear
Parabolic
10.57
10.99
12.34
12.08
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 11a. Glasgow: NAFEMS, Nov., 1987.
Thin Square Cantilevered Plate — Anti-symmetric Modes
This test is a normal mode dynamic analysis of a thin, square, cantilevered plate meshed with shellelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 11b.
Attributes of this test are:
• Anti-symmetric modes
NX Nastran 11 Verification Manual 5-19
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
• nf011b.dat (linear (4-noded) quadrilateral)
• nf011hb.dat (parabolic (8-noded) quadrilateral)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 32 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.05m
• 8 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05m
Mesh only half the plate (10m × 5m).
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z = Ry = Rx = 0 along Y-axis
• Rx = 0 along Y = 5m
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = —1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass)(Hz)
NX NastranResult(coupledmass(Hz)
1 1.029 Linear
Parabolic
1.019
1.018
1.000
1.005
1.020
1.0222 3.753 Linear
Parabolic
3.839
3.710
3.570
3.597
3.767
3.7253 7.730 Linear
Parabolic
8.313
7.768
7.091
7.026
8.113
7.7864 8.561 Linear
Parabolic
9.424
8.483
8.047
8.133
9.025
8.6905 not available Linear
Parabolic
11.73
11.19
9.940
10.15
11.69
11.196 not available Linear
Parabolic
17.82
15.76
14.22
14.21
17.44
16.78
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis Test No. 11b. Glasgow: NAFEMS, Nov., 1987.
NX Nastran 11 Verification Manual 5-21
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Free Thin Square Plate
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 12.
Attributes of this test are:
• Rigid body modes (three modes)
• Repeated eigenvalues
Test Case Data and Information
Input Files
• nf012l_l.dat (linear (4-noded) quadrilateral, lumped mass)
• nf012l_c.dat (linear (4-noded) quadrilateral, coupled mass)
• nf012h_l.dat (parabolic (8-noded) quadrilateral, lumped mass)
• nf012h_c.dat (parabolic (8-noded) quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 64 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.05m
5-22 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• 16 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05m
Boundary Conditions
• X = Y = Rz = 0 at all grid points
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
Results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
4 1.622 Linear
Parabolic
1.632
1.532
1.578
1.584
1.624
1.6195 2.360 Linear
Parabolic
2.402
2.356
2.241
2.233
2.389
2.3636 2.922 Linear
Parabolic
3.006
2.861
2.804
2.808
2.979
2.9297, 8 4.233 Linear
Parabolic
4.251
4.122
3.931
3.944
4.237
4.1589 7.416 Linear
Parabolic
7.859
7.363
6.822
6.813
7.790
7.47710 Not available Linear
Parabolic
8.027
7.392
6.822
6.813
7.790
7.477
NX Nastran 11 Verification Manual 5-23
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 12. Glasgow: NAFEMS, Nov., 1987.
Simply Supported Thin Square Plate
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 13.
Attributes of this test are:
• Well established
• Repeated eigenvalues
Test Case Data and Information
Input Files
• nf013l_l.dat (linear quadrilateral, lumped mass)
• nf013l_c.dat (linear quadrilateral, coupled mass)
• nf013h_l.dat (parabolic quadrilateral, lumped mass)
• nf013h_c.dat (parabolic quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Two tests:
• 64 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.05m
• 16 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05m
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z = Rx = 0 along edges X = 0 and X = 10m
• Z = Ry = 0 along edges Y = 0 and Y = 10m
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
1 2.377 Linear
Parabolic
2.332
2.376
2.392
2.3822, 3 5.942 Linear
Parabolic
5.797
5.938
6.181
6.0264 9.507 Linear
Parabolic
8.963
9.747
9.933
10.22
NX Nastran 11 Verification Manual 5-25
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode ReferenceValue (Hz)
Mesh NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
5, 6 11.88 Linear
Parabolic
11.67
11.87
13.27
12.397, 8 15.45 Linear
Parabolic
14.45
16.56
17.07
18.17
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 13. Glasgow: NAFEMS, Nov., 1987.
Simply Supported Thin Annular Plate
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 14.
Attributes of this test are:
• Curved boundary (skewed coordinate system)
• Repeated eigenvalues
Test Case Data and Information
Input Files
• nf014l_l.dat (linear quadrilateral, lumped mass)
5-26 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• nf014l_c.dat (linear quadrilateral, coupled mass)
• nf014h_l.dat (parabolic quadrilateral, lumped mass)
• nf014h_c.dat (parabolic quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 160 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.06 m
• 48 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.06 m
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z′ = Rx′ = 0 around the circumference
Solution Type
SOL 103 — Normal Mode Dynamics, Lanczos Method
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
NX Nastran 11 Verification Manual 5-27
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode ReferenceValue (Hz)
Mesh NX Nastran Result(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
1 1.870 Linear
Parabolic
1.859
1.840
1.877
1.8732, 3 5.137 Linear
Parabolic
5.293
5.111
5.249
5.1514, 5 9.673 Linear
Parabolic
10.03
9.673
9.983
9.7136 14.85 Linear
Parabolic
14.37
13.95
15.41
14.927, 8 15.57 Linear
Parabolic
16.10
15.55
15.55
15.719 18.38 Linear
Parabolic
18.07
17.38
19.09
18.52
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis,, Test No. 13. Glasgow: NAFEMS, Nov., 1987.
Clamped Thin Rhombic Plate
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 15.
Attributes of this test are:
5-28 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Distorted elements
Test Case Data and Information
Input Files
• nf015l.dat linear (lumped)
• nf015ha.dat parabolic (lumped)
• nf015hb.dat parabolic (consistent)
• nf015hc.data linear (consistent)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 144 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.05 m
• 36 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05 m
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z′ = Rx′ = Ry′ = 0 along all four edges
NX Nastran 11 Verification Manual 5-29
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL103 — Normal Mode Dynamics
NX Nastran results were obtained two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 7.938 Linear
Parabolic
8.142
7.873
7.818
7.902
7.955
7.9292 12.84 Linear
Parabolic
13.89
12.48
12.83
12.85
13.39
13.013 17.94 Linear
Parabolic
20.04
17.31
17.81
17.95
19.07
18.474 19.13 Linear
Parabolic
20.17
18.74
18.55
18.96
19.24
19.175 24.01 Linear
Parabolic
27.70
27.95
23.67
23.88
26.19
25.236 27.92 Linear
Parabolic
32.05
25.88
27.70
27.91
29.82
28.81
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 15. Glasgow: NAFEMS, Nov., 1987.
5-30 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Cantilevered Thin Square Plate with Distorted Mesh
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMSSelected Benchmarks for NaturalFrequency Analysis, Test 16.
Attributes of this test are:
• Distorted meshes
Test Case Data and Information
Input Files
• nf016a1.dat: (16 parabolic quad, lumped mass)
• nf016a2.dat: (16 parabolic quad, coupled mass)
• nf016b1.dat: (16 parabolic quad, lumped mass)
• nf016b2.dat: (16 parabolic quad, coupled mass)
• nf016c1.dat: (4 parabolic quad, lumped mass)
• nf016c2.dat: (4 parabolic quad, coupled mass)
• nf016d1.dat: (4 parabolic quad, lumped mass)
• nf016d2.dat: (4 parabolic quad, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
NX Nastran 11 Verification Manual 5-31
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
All tests — parabolic quadrilateral thin shell elements — thickness = 0.05m
Four tests:
• Test 1 — 16 elements
• Test 2 — 16 elements with specified grid points at the following XY coordinates:
CoordinatesNode X Y1 4.000 4.0002 2.250 2.2503 4.750 2.5004 7.250 2.7505 7.500 7.2506 5.250 7.2507 5.250 7.2508 2.250 7.2509 2.500 4.750
• Test 3 — 4 elements
5-32 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Test 4 — 4 elements with a specified grid point at the following XY coordinate:
CoordinatesNode X Y1 4.000 4.000
Boundary Conditions
• X = Y = Z = Ry = 0 along Y-axis
Solution Type
SOL103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
NX Nastran 11 Verification Manual 5-33
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Test NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 0.4210 1
2
3
4
0.4174
0.4174
0.4144
0.4145
0.4139
0.4135
0.4021
0.4000
0.4181
0.4182
0.4189
0.41922 1.029 1
2
3
4
1.020
1.020
0.9990
1.002
0.9985
0.9967
0.9347
0.9202
1.024
1.024
1.021
1.0253 2.582 1
2
3
4
2.564
2.571
2.554
2.565
2.444
2.445
2.132
2.112
2.569
2.566
2.708
2.6984 3.306 1
2
3
4
3.302
3.317
3.401
3.424
3.082
3.072
2.707
2.697
3.281
3.280
3.449
3.4305 3.753 1
2
3
4
3.769
3.780
3.697
3.714
3.540
3.535
3.136
3.077
3.728
3.731
3.913
3.8816 6.555 1
2
3
4
6.805
6.883
5.455
5.133
6.018
5.994
5.458
5.459
6.551
6.552
7.108
6.858
5-34 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 16. Glasgow: NAFEMS, Nov., 1987.
Simply Supported Thick Square Plate, Test A
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 21a.
Attributes of this test are:
• Well established
• Repeated eigenvalues
• Effect of secondary restraints
Test Case Data and Information
Input Files
• nf021a.dat: linear (lumped mass)
• nf021ha.dat: parabolic (lumped mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
NX Nastran 11 Verification Manual 5-35
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Two tests:
• 64 linear quadrilateral thin shell (CQUAD4) elements — thickness = 1.0 m
• 16 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 1.0 m
Boundary Conditions
• Z = 0 along all four edges
• X = Y = Rz = 0 at all grid points
• Rx = 0 along edges X = 0 and X = 10 m
• Ry = 0 along edges Y = 0 and Y = 10 m
Solution Type
SOL103 — Normal Mode Dynamics
5-36 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 45.90 Linear
Parabolic
46.66
45.94
45.83
46.17
46.35
45.832, 3 109.4 Linear
Parabolic
115.8
110.4
110.6
110.3
114.1
109.44 167.9 Linear
Parabolic
177.5
170.4
164.8
167.3
174.3
169.85, 6 204.5 Linear
Parabolic
233.4
212.8
211.8
204.6
227.1
208.27, 8 256.5 Linear
Parabolic
283.6
270.0
250.5
249.3
276.9
268.49 336.6 Linear
Parabolic
371.1
344.8
313.1
311.4
364.3
319.410 336.6 Linear
Parabolic
371.1
344.8
338.4
347.6
385.8
319.4
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 21a. Glasgow: NAFEMS, Nov., 1987.
Simply Supported Thick Square Plate, Test B
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 21b.
NX Nastran 11 Verification Manual 5-37
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Well established
• Repeated eigenvalues
• Effect of secondary restraints
Test Case Data and Information
Input Files
• nf021b_c.dat (quadrilateral thin shell elements — coupled mass)
• nf021b_l.dat (quadrilateral thin shell elements — lumped mass)
• nf021hb_c.dat (parabolic thin shell elements — coupled mass)
• nf021hb_l.dat (parabolic thin shell elements — lumped mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 64 linear quadrilateral thin shell elements — thickness = 1.0 m
• 16 parabolic quadrilateral thin shell elements — thickness = 1.0 m
5-38 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• Z = 0 along all four edges; X = Y = Rz = 0 at all grid points
Solution Type
SOL103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
NX Nastran 11 Verification Manual 5-39
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 45.90 Linear
Parabolic
44.75
44.13
44.65
44.82
44.96
44.492, 3 109.4 Linear \
Parabolic
112.9
107.9
109.1
108.5
112.3
107.64 167.9 Linear
Parabolic
170.3
164.2
161.4
163.6
170.2
165.75, 6 204.5 Linear
Parabolic
230.2
20.07
210.5
203.1
225.4
206.57, 8 256.5 Linear
Parabolic
274.2
260.3
247.1
245.7
272.5
263.69 336.6 Linear
Parabolic
356.0
342.8
308.8
307.2
358.4
318.610 336.6 Linear
Parabolic
356.0
342.8
337.6
346.9
384.8
318.6
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 21b. Glasgow: NAFEMS, Nov., 1987.
Clamped Thick Rhombic Plate
This test is a normal mode dynamic analysis of a free thin square plate meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 22.
5-40 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Distorted elements
Test Case Data and Information
Input Files
• nf022l_l.dat
• nf022l_c.dat
• nf022h_l.dat
• nf022h_c.dat
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 100 linear quadrilateral thin shell (CQUAD4) elements - thickness = 1.0 m
• 36 parabolic quadrilateral thin shell (CQUAD8) elements - thickness = 1.0 m
NX Nastran 11 Verification Manual 5-41
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z′ = Rx′ = Ry′ = 0 along all four edges
Solution Type
SOL 103 – Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (parm coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 134.0 Linear
Parabolic
137.8
133.9
131.2
134.9
134.3
135.22 201.4 Linear
Parabolic
218.5
203.3
200.4
204.4
211.9
206.33 265.8 Linear
Parabolic
295.4
271.4
262.0
270.3
286.6
276.4
5-42 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
4 282.7 Linear
Parabolic
296.8
283.7
273.6
286.9
287.0
289.15 334.5 Linear
Parabolic
383.6
346.4
327.0
337.5
373.3
353.86 Not available Linear
Parabolic
426.6
386.6
372.2
384.7
410.6
394.0
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N.C.,Selected Benchmarks for Natural Frequency Analysis, Test No. 22. Glasgow: NAFEMS, Nov.,1987.
Simply Supported Thick Annular Plate
This test is a normal mode dynamic analysis of a simply supported thick annular plate meshedwith shell elements. This document provides the input data and results for NAFEMS SelectedBenchmarks for Natural Frequency Analysis, Test 23.
Attributes of this test are:
• Curved boundary (skewed coordinate system)
• Repeated eigenvalues
NX Nastran 11 Verification Manual 5-43
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
nf023l_l.dat
nf023l_c.dat
nf023h_l.dat
nf023h_c.dat
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 160 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.6 m
• 48 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.6 m
Boundary Conditions
• X = Y = Rz = 0 at all grid points
• Z′ = Rx′ = 0 around the circumference
5-44 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmas = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass(Hz)
1 18.58 Linear
Parabolic
18.82
18.59
18.40
18.53
18.64
18.652, 3 48.92 Linear
Parabolic
49.82
49.02
50.00
49.22
50.81
49.414, 5 92.59 Linear
Parabolic
96.06
92.90
93.09
93.41
96.00
93.736 140.2 Linear
Parabolic
148.3
140.9
134.6
140.2
147.0
143.17, 8 Not available Linear
Parabolic
153.7
146.6
144.0
147.0
152.1
148.29 166.4 Linear
Parabolic
174.5
167.3
162.2
166.9
177.1
170.4
NX Nastran 11 Verification Manual 5-45
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 23. Glasgow: NAFEMS, Nov., 1987.
Cantilevered Square Membrane
This test is a normal mode dynamic analysis of a cantilevered square membrane meshed with shellelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 31.
Attributes of this test are:
• Well established
Test Case Data and Information
Input Files
• nf031l.dat (linear quadrilateral, lumped mass)
• nf031a.dat (linear quadrilateral, coupled mass)
• nf031h.dat (parabolic quadrilateral, lumped mass)
• nf031j.dat (parabolic quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
5-46 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Two tests:
• 64 linear quadrilateral thin shell (CQUAD4) elements - thickness = 0.05 m
• 16 parabolic quadrilateral thin shell (CQUAD8) elements - thickness = 0.05 m
Boundary Conditions
• X = Y = 0 along the Y axis
• Z = 0 at all grid points
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
NX Nastran 11 Verification Manual 5-47
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 52.40 Linear
Parabolic
52.91
52.64
52.48
52.30
52.78
52.602 125.7 Linear
Parabolic
126.1
125.9
125.6
125.7
126.1
125.93 140.8 Linear
Parabolic
143.2
141.5
139.6
139.5
142.9
141.44 222.5 Linear
Parabolic
228.9
224.6
215.1
214.4
227.5
224.35 241.4 Linear
Parabolic
247.9
243.3
240.1
242.3
247.4
242.96 255.7 Linear
Parabolic
260.6
256.8
252.4
254.6
259.8
256.6
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 31. Glasgow: NAFEMS, Nov., 1987.
Cantilevered Tapered Membrane
This test is a normal mode dynamic analysis of a cantilevered tapered membrane meshed with shellelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 32.
Attributes of this test are:
5-48 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Shear behavior
• Irregular mesh
• Symmetry
Test Case Data and Information
Input Files
• nf032l.dat (linear quadrilateral, lumped mass)
• nf032a.dat (linear quadrilateral, coupled mass)
• nf032h.dat (parabolic quadrilateral, lumped mass)
• nf032j.dat (parabolic quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 128 linear quadrilateral thin shell (CQUADR) elements — thickness = 0.1 m
• 32 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.1 m
NX Nastran 11 Verification Manual 5-49
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• X = Y = 0 along the Y axis
• Z = 0 at all grid points
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmas = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 44.62 Linear
Parabolic
44.91
44.64
44.66
44.54
44.78
44.632 130.0 Linear
Parabolic
132.1
130.1
130.3
129.7
131.8
130.13 162.7 Linear
Parabolic
162.8
162.7
162.6
162.7
162.8
162.74 246.1 Linear
Parabolic
253.0
246.6
246.1
245.1
252.3
246.45 379.9 Linear
Parabolic
393.3
382.0
377.9
377.9
393.2
381.4
5-50 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
6 391.4 Linear
Parabolic
396.3
391.6
389.7
390.9
395.0
391.5
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 32. Glasgow: NAFEMS, Nov., 1987.
Free Annular Membrane
This test is a normal mode dynamic analysis of a free annular membrane meshed with shell elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 33.
Attributes of this test are:
• Repeated eigenvalues
• Rigid body modes (three modes)
Test Case Data and Information
Input Files
• nf033l.dat (linear quadrilateral, lumped mass)
• nf033a.dat (linear quadrilateral, coupled mass)
NX Nastran 11 Verification Manual 5-51
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• nf033h.dat (parabolic quadrilateral, lumped mass)
• nf033j.dat (parabolic quadrilateral, coupled mass)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Two tests:
• 160 linear quadrilateral thin shell (CQUAD4) elements — thickness = 0.06 m
• 48 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.06 m
5-52 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• Z = 0 at all grid points
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
NX Nastran 11 Verification Manual 5-53
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
4, 5 129.2 Linear
Parabolic
129.5
126.5
127.8
125.7
128.8
125.86 226.2 Linear
Parabolic
225.5
224.3
224.5
224.0
225.3
224.27, 8 234.7 Linear
Parabolic
234.9
233.0
229.9
230.8
234.9
233.09, 10 264.7 Linear
Parabolic
272.1
264.8
264.3
262.6
271.2
263.611, 12 336.6 Linear
Parabolic
340.3
335.7
329.0
331.5
339.9
335.713, 14 376.8 Linear
Parabolic
392.0
378.6
369.9
373.3
390.5
377.4
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 33. Glasgow: NAFEMS, Nov., 1987.
Cantilevered Thin Square Plate
This test is a normal mode dynamic analysis of a cantilevered thin square plate meshed with shellelements. This document provides the input data and results for NAFEMSSelected Benchmarks forNatural Frequency Analysis, Test 73.
5-54 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
• nf073a.dat (Test 1)
• nf073b.dat (Test 2)
• nf073c.dat (Test 3)
• nf073d.dat (Test 4)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
16 parabolic quadrilateral thin shell (CQUAD8) elements — thickness = 0.05 m
Boundary Conditions
X = Y = Z = Ry = 0 along the Y axis
NX Nastran 11 Verification Manual 5-55
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
1 0.4210 Test 1
Test 2
Test 3
Test 4
0.4174
0.4174
0.4175
0.4184
0.4154
0.4154
0.4154
0.4161
0.4183
0.4183
0.4184
0.41922 1.029 Test 1
Test 2
Test 3
Test 4
1.020
1.020
1.021
1.032
1.051
1.006
1.007
1.015
1.023
1.023
1.027
1.0243 2.582 Test 1
Test 2
Test 3
Test 4
2.564
2.597
2.677
2.850
2.485
2.509
2.524
2.563
2.579
2.605
2.675
2.6724 3.306 Test 1
Test 2
Test 3
Test 4
3.302
3.345
3.365
3.571
3.150
3.180
3.196
3.373
3.298
3.332
3.344
3.5355 3.753 Test 1
Test 2
Test 3
Test 4
3.769
3.888
4.035
5.466
3.622
3.713
3.828
4.935
3.765
3.862
4.000
5.360
5-56 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX NastranResult(coupledmass) (Hz)
6 376.8 Test 1
Test 2
Test 3
Test 4
6.805
7.517
7.495
——
6.292
6.901
6.879
——
6.719
7.399
7.387
——
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 73. Glasgow: NAFEMS, Nov., 1987.
Axisymmetric Solid and Solid Element Test Cases
Free Cylinder — Axisymmetric Vibration
This test is a normal mode dynamic analysis of a free cylinder meshed with axisymmetric elements.This document provides the input data and results for NAFEMS Selected Benchmarks for NaturalFrequency Analysis, Test 41.
Attributes of this test are:
• Rigid body modes (one mode)
• Coupling between axial, radial, and circumferential behavior
• Close eigenvalues
Test Case Data and Information
Input Files
• nf041l.dat (linear axisymmetric, lumped mass, CQUADX4)
• nf041lt.dat (linear axisymmetric, lumped mass, CTRAX3)
• nf041a.dat (linear axisymmetric, coupled mass, CQUADX4)
NX Nastran 11 Verification Manual 5-57
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• nf041at.dat (linear axisymmetric, coupled mass, CTRAX3)
• nf041h.dat (parabolic axisymmetric, lumped mass, CQUADX8)
• nf041ht.dat (parabolic axisymmetric, lumped mass, CTRAX6)
• nf041j.dat (parabolic axisymmetric, coupled mass, CQUADX8)
• nf041jt.dat (parabolic axisymmetric, coupled mass, CTRAX6)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg / m3
• ν = 0.3
Finite Element Modeling
Four meshes:
• 48 axisymmetric solid linear quadrilateral (CQUADX4) elements
• 96 axisymmetric solid linear triangular (CTRAX3) elements
• 8 axisymmetric solid parabolic quadrilateral (CQUADX8) elements
• 16 axisymmetric solid parabolic triangular (CTRAX6) elements
Boundary Conditions
Unsupported
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode # ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult (lumpedmass) (Hz)
NX NastranResult (coupledmass) (Hz)
2 243.5 CQUADX4CTRAX3CQUADX8CTRAX6
244.0244.0243.5243.5
243.2243.3243.2243.4
244.0244.1243.5243.5
3 377.4 CQUADX4CTRAX3CQUADX8CTRAX6
379.4379.4377.5377.5
370.9377.7356.5376.5
378.1380.9377.5377.5
4 394.1 CQUADX4CTRAX3CQUADX8CTRAX6
395.4395.4394.3394.3
379.3391.4356.9385.7
394.4397.0394.3394.3
5 397.7 CQUADX4CTRAX3CQUADX8CTRAX6
401.4401.4397.9397.9
385.9395.6375.9386.7
398.0408.7398.0398.1
6 405.3 CQUADX4CTRAX3CQUADX8CTRAX6
421.9421.9406.4406.4
389.6423.0393.7397.1
406.8430.4406.4407.3
Note
The reference value refers to the accepted solution to the problem.
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 41. Glasgow: NAFEMS, Nov., 1987.
Thick Hollow Sphere — Uniform Radial Vibration
This test is a normal mode dynamic analysis of a thick hollow sphere meshed using axisymmetricelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 42.
NX Nastran 11 Verification Manual 5-59
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Curved boundary (skewed coordinate system)
• Constraint equations
Test Case Data and Information
Input Files
• nf042l.dat (linear axisymmetric, lumped mass, CQUADX4)
• nf042lt.dat (linear axisymmetric, lumped mass, CTRAX3)
• nf042a.dat (linear axisymmetric, coupled mass, CQUADX4)
• nf042at.dat (linear axisymmetric, coupled mass, CTRAX3)
• nf042h.dat (parabolic axisymmetric, lumped mass, CQUADX8)
• nf042ht.dat (parabolic axisymmetric, lumped mass, CTRAX6)
• nf042j.dat (parabolic axisymmetric, coupled mass, CQUADX8)
• nf042jt.dat (parabolic axisymmetric, coupled mass, CTRAX6)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
5-60 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Four meshes:
• 10 axisymmetric solid linear quadrilateral (CQUADX4) elements -α = 5°
• 20 axisymmetric solid linear triangular (CTRAX3) elements -α = 5°
• 10 axisymmetric solid parabolic quadrilateral (CQUADX8) elements -α = 5°
• 20 axisymmetric solid parabolic triangular (CTRAX6) elements -α = 5°
Boundary Conditions
• Z′ displacement = 0 at all grid points
• Grid points at the same R′ are constrained to have the same r′ displacement
• One constraint set
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
NX Nastran 11 Verification Manual 5-61
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode # ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult (lumpedmass) (Hz)
NX NastranResult (coupledmass) (Hz)
1 369.9 CQUADX4CTRAX3CQUADX8CTRAX6
370.6370.6370.0370.0
370.0370.5369.4369.7
370.0370.7369.8369.8
2 838.0 CQUADX4CTRAX3CQUADX8CTRAX6
841.2841.2838.1838.1
831.8834.0832.7835.9
839.4842.7837.7837.7
3 1451. CQUADX4CTRAX3CQUADX8CTRAX6
1473.1473.1453.1453.
1421.1424.1434.1446.
1471.1475.1451.1451.
4 2117. CQUADX4CTRAX3CQUADX8CTRAX6
2192.2192.2132.2132.
2031.2033.2073.2105.
2189.2194.2117.2117.
5 2796. CQUADX4CTRAX3CQUADX8CTRAX6
2976.2976.2853.2853.
2604.2607.2706.2773.
2971.2978.2799.2799.
Note
The reference value refers to the accepted solution to the problem.
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis Test No. 42. Glasgow: NAFEMS, Nov., 1987.
Simply Supported Annular Plate — Axisymmetric Vibration
This test is a normal mode dynamic analysis of a simply supported annular plate meshed withaxisymmetric elements. This document provides the input data and results for NAFEMS SelectedBenchmarks for Natural Frequency Analysis, Test 43.
5-62 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Well established
Test Case Data and Information
Input Files
• nf043a.dat (linear axisymmetric, lumped mass, CQUADX4)
• nf043at.dat (linear axisymmetric, lumped mass, CTRAX3)
• nf043b.dat (linear axisymmetric, coupled mass, CQUADX4)
• nf043bt.dat (linear axisymmetric, coupled mass, CTRAX3)
• nf043c.dat (parabolic axisymmetric, lumped mass, CQUADX8)
• nf043ct.dat (parabolic axisymmetric, lumped mass, CTRAX6)
• nf043d.dat (parabolic axisymmetric, coupled mass, CQUADX8)
• nf043dt.dat (parabolic axisymmetric, coupled mass, CTRAX6)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
NX Nastran 11 Verification Manual 5-63
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Four meshes:
• 60 axisymmetric solid linear quadrilateral (CQUADX4) elements
• 120 axisymmetric solid linear triangular (CTRAX3) elements
• 5 axisymmetric solid parabolic quadrilateral (CQUADX8) elements
• 10 axisymmetric solid linear triangular (CTRAX6) elements
Boundary Conditions
• Z = 0 at A
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
5-64 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode # ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult (lumpedmass) (Hz)
NX NastranResult(coupled mass)(Hz)
1 18.54 CQUADX4CTRAX3CQUADX8CTRAX6
18.7118.7118.5818.58
18.5418.7218.4318.53
18.5718.7518.5818.60
2 150.2 CQUADX4CTRAX3CQUADX8CTRAX6
145.5145.5145.6145.6
138.6160.2136.0139.0
140.2162.0140.6141.0
3 224.2 CQUADX4CTRAX3CQUADX8CTRAX6
224.2224.2224.2224.2
224.2224.2224.0224.1
224.2224.3224.2224.2
4 358.3 CQUADX4CTRAX3CQUADX8CTRAX6
385.6385.6374.1374.1
361.5417.8353.6369.7
371.5429.3374.0379.3
5 629.2 CQUADX4CTRAX3CQUADX8CTRAX6
689.3689.3686.0686.0
643.3687.5633.1680.5
673.8690.3686.0688.5
Note
The reference value refers to the accepted solution to the problem.
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 43. Glasgow: NAFEMS, Nov., 1987.
Deep Simply Supported "Solid" Beam
This test is a normal mode dynamic analysis of a deep, simply supported beam meshed with solidelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis , Test 51.
NX Nastran 11 Verification Manual 5-65
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Skewed coordinate system
• Skewed restraints
Test Case Data and Information
Input Files
• nf051a.dat (linear brick)
• nf051b.dat (parabolic brick)
• nf051c.dat (linear pyramid)
• nf051d.dat (parabolic pyramid)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
5-66 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Four tests:
• 30 solid linear brick (CHEXA) elements
• 5 solid parabolic brick (CHEXA) elements
• 180 solid linear pyramid (CPYRAM) elements (created by dividing each linear brick elementinto 6 pyramid elements)
• 30 solid parabolic pyramid (CPYRAM) elements (created by dividing each parabolic brick elementinto 6 pyramid elements)
Boundary Conditions
• X′ = Z′ = 0 along AA′
• Z′ = 0 along BB′
• Y′ = 0 at all grid points on the plane Y′ = 2.0 m
NX Nastran 11 Verification Manual 5-67
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode # ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult (lumpedmass) (Hz)
NX NastranResult(coupled mass)(Hz)
1 38.20 linear brick
linear pyramid
parabolic brick
parabolicpyramid
42.88
38.82
37.96
41.30
37.85
37.90
38.28
41.50
38.24
38.10
2 85.21 linear brick
linear pyramid
parabolic brick
parabolicpyramid
93.82
88.45
83.38
89.30
87.12
86.30
83.95
89.60
87.52
86.50
3 152.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
170.7
159.4
152.7
163.0
151.8
152.0
157.6
166.0
157.0
155.0
4 245.5 linear brick
linear pyramid
parabolic brick
parabolicpyramid
286.1
259.2
251.6
269.0
248.5
250.0
264.9
276.0
258.2
255.0
5 297.1 linear brick
linear pyramid
parabolic brick
parabolicpyramid
318.9
307.9
288.0
303.0
289.6
291.0
298.3
309.0
305.6
300.0
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Note
The reference value refers to the accepted solution to the problem.
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.,Selected Benchmarks for Natural Frequency Analysis Test No. 51. Glasgow: NAFEMS, Nov., 1987.
Simply Supported "Solid" Square Plate
This test is a normal mode dynamic analysis of a simply supported square plate meshed with solidelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 52.
Attributes of this test are:
• Well established
• Rigid body modes (three modes)
• Kinematically incomplete suppressions
Test Case Data and Information
Input Files
• nf052l.dat (linear brick)
• nf052b.dat (parabolic brick)
• nf052c.dat (linear pyramid)
• nf052d.dat (parabolic pyramid)
Units
SI
Material Properties
• E = 200E09 N/m2
NX Nastran 11 Verification Manual 5-69
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Four tests:
• 64 solid linear brick (CHEXA) elements
• 16 solid parabolic brick (CHEXA) elements
• 384 solid linear pyramid (CPYRAM) elements (created by dividing each linear brick elementinto 6 pyramid elements)
• 96 solid parabolic pyramid (CPYRAM) elements (created by dividing each parabolic brick elementinto 6 pyramid elements)
Boundary Conditions
Z = 0 along the four edges on the plane Z = –0.5 m
5-70 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Solution Type
SOL 103 normal modes
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
Results
Mode # ReferenceValue(Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
4 45.90 linear brick
linear pyramid
parabolic brick
parabolicpyramid
51.65
44.76
44.04
66.90
43.81
44.70
45.24
68.00
44.16
44.80
5, 6 109.4 linear brick
linear pyramid
parabolic brick
parabolicpyramid
132.7
110.5
106.5
154.0
105.2
109.0
113.7
160.0
107.9
110.0
7 167.9 linear brick
linear pyramid
parabolic brick
parabolicpyramid
194.4
169.1
155.5
195.0
156.3
166.0
172.3
197.0
163.9
169.0
8 193.6 linear brick
linear pyramid
parabolic brick
parabolicpyramid
197.2
193.9
193.6
207.0
194.0
194.0
196.8
212.0
193.9
194.0
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Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Mode # ReferenceValue(Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumped mass)(Hz)
NX Nastran Result(coupled mass)(Hz)
9 206.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
210.6
206.6
200.1
207.0
193.5
196.0
209.6
212.0
206.6
207.0
10 206.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
210.6
206.6
200.1
220.0
193.5
196.0
209.6
223.0
206.6
207.0
Note
The reference value refers to the accepted solution to the problem.
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 52. Glasgow: NAFEMS, Nov., 1987.
Simply Supported "Solid" Annular Plate
This test is a normal mode dynamic analysis of a simply supported annular plate meshed with solidelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 53.
Attributes of this test are:
• Curved boundary (skewed coordinate system)
5-72 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
• Constraint equations
Test Case Data and Information
Input Files
• nf053l.dat (linear brick)
• nf053h.dat (parabolic brick)
• nf053c.dat (linear pyramid)
• nf053d.dat (parabolic pyramid)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 0.3
Finite Element Modeling
Four tests:
• 60 solid linear brick (CHEXA) elements — α = 5°
• 5 solid parabolic brick (CHEXA) elements — α = 10°
• 360 solid linear pyramid (CPYRAM) elements (created by dividing each linear brick elementinto 6 pyramid elements)
• 30 solid parabolic pyramid (CPYRAM) elements (created by dividing each parabolic brick elementinto 6 pyramid elements)
NX Nastran 11 Verification Manual 5-73
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• θ displacement = 0 at all grid points
• Z displacement = 0 at all grid points along AA
• Grid points at same R and Z are constrained to have same z displacement
• One constraint set
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
5-74 NX Nastran 11 Verification Manual
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode # ReferenceValue (Hz)
Mesh NAFEMSTarget Value(Hz)
NX NastranResult(lumpedmass) (Hz)
NX Nastran Result(coupled mass) (Hz)
1 18.58 linear brick
linear pyramid
parabolic brick
parabolicpyramid
19.66
18.58
18.57
19.90
18.45
21.30
18.61
19.90
18.58
21.50
2 140.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
146.4
140.4
138.8
147.0
135.9
140.0
140.5
148.0
140.3
143.0
3 224.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
224.3
224.2
224.2
224.0
223.7
224.0
224.4
224.0
224.2
225.0
4 358.3 linear brick
linear pyramid
parabolic brick
parabolicpyramid
386.7
374.0
361.8
383.0
351.2
359.0
372.1
390.0
371.9
376.0
5 629.2 linear brick
linear pyramid
parabolic brick
parabolicpyramid
689.5
686.0
643.8
684.0
624.7
640.0
674.7
690.0
679.6
683.0
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 53. Glasgow: NAFEMS, Nov., 1987.
NX Nastran 11 Verification Manual 5-75
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Cantilevered Solid Beam
This test is a normal mode dynamic analysis of a cantilevered solid beam meshed using solidelements. This document provides the input data and results for NAFEMS Selected Benchmarks forNatural Frequency Analysis, Test 72.
Attributes of this test are:
• Highly populated stiffness matrix
Test Case Data and Information
Input Files
• nf072a.dat (parabolic bricks – conventional)
• nf072b.dat (parabolic bricks – unconventional)
• nf072c.dat (parabolic pyramids – conventional)
• nf072d.dat (parabolic pyramids – unconventional)
Units
SI
Material Properties
• E = 200E09 N/m2
• ρ = 8000 kg/m3
• ν = 3
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
Four tests:
• Test 1: solid parabolic brick (CHEXA) elements, conventional grid point numbering
• Test 2: solid parabolic pyramid (CPYRAM) elements (created by dividing each brick element into6 pyramid elements), conventional grid point numbering
• Test 3: solid parabolic brick (CHEXA) elements, unconventional grid point numbering
• Test 4: solid parabolic pyramid (CPYRAM) elements (created by dividing each brick element into6 pyramid elements), unconventional grid point numbering
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Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• X = Y = Z = 0 at all grid points on X = 0 plane
• Y = 0 at grid points on Y = 1 m plane
Solution Type
SOL 103 — Normal Mode Dynamics
NX Nastran results were obtained in two different ways:
• Using lumped mass (param coupmass = –1)
• Using coupled mass (param coupmass = 1)
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Chapter 5: Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Results
Mode # Mesh NAFEMS TargetValue (Hz)
NX NastranResult (lumpedmass) (Hz)
NX Nastran Result(coupled mass)(Hz)
1 Test 1
Test 2
Test 3
Test 4
16.01
16.01
15.82
15.90
15.82
15.90
15.99
16.00
15.99
16.002 Test 1
Test 2
Test 3
Test 4
87.23
87.23
83.18
84.30
83.18
84.30
87.09
87.00
87.09
87.003 Test 1
Test 2
Test 3
Test 4
126.0
126.0
125.5
126.0
125.5
126.0
126.0
126.0
126.0
126.04 Test 1
Test 2
Test 3
Test 4
209.6
209.6
193.5
198.0
193.5
198.0
209.1
209.0
209.1
209.05 Test 1
Test 2
Test 3
Test 4
351.1
351.1
310.1
323.0
310.1
323.0
349.9
350.0
349.9
350.06 Test 1
Test 2
Test 3
Test 4
375.8
375.8
364.2
367.0
364.2
367.0
375.8
375.0
375.8
375.0
References
NAFEMS Finite Element Methods & Standards, Abbassian, F., Dawswell, D. J., and Knowles, N. C.Selected Benchmarks for Natural Frequency Analysis, Test No. 72. Glasgow: NAFEMS, Nov., 1987.
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Normal Mode Dynamics Verification Using Standard NAFEMS Benchmarks
Chapter 6: Verification Test Cases from the SocieteFrancaise des Mecaniciens
6.1 Overview of Verification Test Cases Provided by the SocieteFrancaise des MecaniciensThe purpose of these linear statics test cases is to verify the function of NX Nastran using standardbenchmarks published by SFM (Societe Francaise des Mecaniciens. Paris, France) in Guide devalidation des progiciels de calcul de structures.
Included here are:
• Tests cases on mechanical structures using linear statics analysis, normal mode dynamicsanalysis, and model response.
• Stationary thermal test cases using heat transfer analysis.
• Thermo-mechanical test cases using linear statics analysis.
Results published in Guide de validation des progiciels de calcul de structures are compared withthose computed using NX Nastran.
Understanding the Test Case Format
Each test case is structured with the following information.
• Test case data and information:
o Input files
o Units
o Material properties
o Finite element modeling information
o Boundary conditions (loads and restraints)
o Solution type
• Results
• Reference
Reference
The following reference has been used in these test cases:
NX Nastran 11 Verification Manual 6-1
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures.Paris, Afnor Technique, 1990.
Mechanical Structures — Linear Statics Analysis with Beam or RodElements
Short Beam on Two Articulated Supports
This test is a linear statics analysis of a short, straight beam with plane bending and shear loading.It provides the input data and results for benchmark test SSLL02/89 from Guide de validation desprogiciels de calcul de structures.
• Area = 31E–04 m2
• Inertia = 2810E–08 m4
• Shear area ratio = 2.42
Test Case Data and Information
Input Files
ssll02.dat
Units
SI
Material Properties
• E = 2E11 Pa
• ν = 0.3
Finite Element Modeling
• 10 linear beam (CBAR) elements
• 11 grid points
The mesh is shown in the following figure:
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Restrain both free ends of the beam in translation DOF.
o Edge load = 1E05 N/m in –Y direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result Bench Value NX NastranDisplacement at point B v (m) (Grid point 7) –1.259E–3 –1.249E–3
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLL02/89.
Clamped Beams Linked by a Rigid Element
This test is a linear statics analysis of a straight, cantilever beam with plane bending and a rigidelement. It provides the input data and results for benchmark test SSLL05/89 from Guide devalidation des progiciels de calcul de structures.
Test Case Data and Information
Input File
ssll05.dat
Units
SI
NX Nastran 11 Verification Manual 6-3
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 2E11 Pa
• I = (4/3)E–08 m4
Finite Element Modeling
• 20 linear beam (CBAR) elements
• 1 rigid element
• 26 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Points A and C: Clamped
• Point D: Set nodal force = 1000 N in –Y direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid point Point BenchValue
NX Nastran
v (m) Disp. Y Grid point 6 B –0.1250 –0.1250v (m) Disp. Y Grid point 3 D –0.1250 –0.1250V force (N) Y Grid point 1 A 500.0 500.0M moment (Nm) Rz Grid point 1 A 500.0 500.0V force (N) Y Grid point 4 C 500.0 500.0
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Type Grid point Point BenchValue
NX Nastran
M moment (Nm) Rz Grid point 4 C 500.0 500.0
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990 Test No. SSLL05/89.
Transverse Bending of a Curved Pipe
This test is a linear statics analysis (three-dimensional problem) of a curved pipe with transversebending and bending-torque loading. It provides the input data and results for benchmark testSSLL07/89 from Guide de validation des progiciels de calcul de structures.
• R = 1 m
• de = 0.02 m
• di = 0.016 m
• A = 1.131E-0–04 m2
• Ix = 4.637E–09 m4
Test Case Data and Information
Input Files
• ssll07a.dat linear beam
• ssll07b.dat curved beam
Units
SI
NX Nastran 11 Verification Manual 6-5
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 2E11 Pa
• ν = 0.3
Finite Element Modeling
Test 1
• 90 linear beam (CBAR) elements
• 91 grid points
Test 2
• 90 curved beam (CBEND) elements
• 91 grid points
To obtain the point where θ = 15° with accuracy, use surface mapped meshing on 1/4 of a cylinder.Then mesh a curved edge with the Surface Coating command and undo the mesh on the surface.
The mesh for Test 1 is shown in the following figure:
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Clamp point A.
• Grid point force F = 100 N in Z direction.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid point Point BenchValue
TestNumber
NX Nastran
u (m) Disp. Z Grid point 1 B 0.1346 1 0.1346
2 0.1346Mt (Nm)* Grid point 1 θ = 15° 74.12 1 76.67
2 77.51Mf (Nm) –96.59 1 –96.37
2 –95.70
Mf = bending moment
Mt = torsional moment
*See "Post Processing" below.
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Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Post Processing
Linear Beam (CBAR) Elements
List beam forces on element 167, second end:
• Mf = torque
• Mt = bending moment
Curved Beam (CBEND) Elements
List beam forces on element 166, second end:
• Mf = torque
• Mt = bending moment
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990.Test No. SSLL07/89..
Plane Bending Load on a Thin Arch
This test is a linear statics analysis (plane problem) of a thin arc with plane bending. It provides theinput data and results for benchmark test SSLL08/89 from Guide de validation des progiciels decalcul de structures.
• R = 1 m
• de = 0.02 m
• di = 0.016 m
• A = 1.131E–04 m2
• Ix 4.637E–09 m4
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input File
ssll08.dat
Units
SI
Material Properties
• E = 2E11 Pa
• ν = 0.3
Finite Element Modeling
• 10 linear beam (CBAR) elements
• 11 grid points
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Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Point A: Articulated Z
• Point B: Sets Y and Z displacement to 0
• Force = 100N in –Y direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid Point Point Bench Value NX NastranRz (rad) 2 A –3.077E–2 –3.110E–2Rz (rad) 1 B 3.077E–2 3.110E–2Y (m) 7 C -1.921E–2 –1.934E–2X (m) 1 B 5.391E-2 5.374E–2
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLL08/89.
Grid Point Load on an Articulated CONROD Truss
This test is a linear statics analysis of a plane truss with an articulated rod. It provides the input dataand results for benchmark test SSLL11/89 from Guide de validation des progiciels de calcul destructures.
6-10 NX Nastran 11 Verification Manual
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input File
ssll11.dat
Units
SI
Material Properties
• E = 1.962E11 Pa
NX Nastran 11 Verification Manual 6-11
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 4 rod (CONROD) elements
• 4 grid points
The mesh is shown in the following figure:
Element Length (m) Area (m2)AC 2.000E–4
CB 2.000E–4
CD 1.000E–4
BD 1.000E–4
Boundary Conditions
• Point A and B: Articulated
• Point D: Set Nodal force = 9.81 E3 N in –Y direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Results
Type Grid Point Point Bench Value NX NastranX (m) 18.00 C 0.2652E–3 0.2652E–3Y (m) 18.00 C 0.08839E–3 0.08839E–3X (m) 2.000 D 3.479E–3 3.479E–3Y (m) 2.000 D –5.601E–3 –5.600E–3
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures.(Paris, Afnor Technique, 1990..) Test No. SSLL11/89.
Articulated Plane Truss
This test is a linear statics analysis of a straight cantilever beam with plane bending andtension-compression. It provides the input data and results for benchmark test SSLL14/89 from Guidede validation des progiciels de calcul de structures.
• I1 = 5E–04 m4
• I2 = 2.5E–04 m4
NX Nastran 11 Verification Manual 6-13
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input Files
• ssll14a.dat (4 elements)
• ssll14b.dat (10 elements)
Units
SI
Material Properties
• E = 2.1E11 Pa
Finite Element Modeling
Test 1
• 4 linear beam (CBAR) elements
• 5 grid points
Test 2
• 10 linear beam (CBAR) elements
• 11 grid points
The mesh for Test 2 is shown in the following figure:
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Point A and B: Articulate
• Set forces and moments to the following numeric values:
o p = –3,000 N/m
o F1 = –20,000 N
o F2 = –10,000 N
o M = –100,000 Nm
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid Point Point Bench Value TestNumber
NX Nastran
Vertical reaction(N)
1.000 A 3.150E4 1
2
3.150E4
3.320E4Hortizontalreaction (N)
1.000 A 2.024E4 1
2
1.920E4
2.061E4VerticalDisplacement (m)
8.000 C 0.03072 1
2
–0.02100
–0.03161
Note
NX Nastran takes shear effect into account.
NX Nastran 11 Verification Manual 6-15
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLL14/89.
Beam on an Elastic Foundation
This test is a linear statics analysis (plane problem) of a straight beam with plane bending and anelastic support. It provides the input data and results for benchmark test SSLL16/89 from Guide devalidation des progiciels de calcul de structures.
Test Case Data and Information
Input File
ssll16.dat
Units
SI
Material Properties
• E = 2.1E11 Pa
• K = 8.4E05 N/m2
• Each spring stiffness is set to: K * L/(number of spring elements).
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 50 linear beam (CBAR) elements
• 49 spring (CBUSH) elements
• 51 grid points
The mesh is shown in the following figure:
NX Nastran 11 Verification Manual 6-17
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Point A and B: Articulated
• Set forces and moments to the following numeric values:
–F = –10000 N
–p = –5000 N/m
–M = 15000 Nm.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Point Bench Value NX NastranRotation(rad) Rz A —0.003050 –0.003034Vertical Reaction force (N) 1.167E4 1.158E4Vertical Disp. (m) D –0.4233E–2 –0.4216E–2
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Type Point Bench Value NX NastranM moment (Nm)* 3.384E4 3.369E4
*List beam forces on element 26, first end, z bending moment.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLL16/89.
Mechanical Structures — Linear Statics Analysis with Shell Elements
Plane Shear and Bending Load on a Plate
This test is a linear statics analysis (plane problem) of a plate with plane bending. It provides theinput data and results for benchmark test SSLP01/89 from Guide de validation des progiciels decalcul de structures.
• Thickness = 1 mm
Test Case Data and Information
Input File
sslp01.dat
Units
SI
Material Properties
• E = 3E10 Pa
• ν = 0.25
NX Nastran 11 Verification Manual 6-19
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 126 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Clamped Plate
• Set a shear force with parabolic distribution on width and constant distribution on thickness.
• Resultant force: p = 40 N.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid point # Location Bench Value NX NastranY (mm) Grid point 3 (L,y) 0.3413 0.3408
Displacement is shown in the following figure:
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990 Test No. SSLP01/89.
Infinite Plate with a Circular Hole
This test is a linear statics analysis (plane problem) of a plate with tension-compression and amembrane effect. It provides the input data and results for benchmark test SSLP02/89 from Guide devalidation des progiciels de calcul de structures.
NX Nastran 11 Verification Manual 6-21
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input File
sslp02.dat
Units
SI
Material Properties
• E = 3E10 Pa
• ν = 0.25
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
The plate is meshed using the biasing option.
The mesh is shown in the following figure:
Boundary Conditions
• u (0,y) = 0, Ry (y) = 0, Rz (y) = 0, (z = 0, all grid points)
• ν (x,0) = 0, Rx (x) = 0, Rz (x) = 0
• Tension force P = 2.5 N/mm**2 (in plane force of 2500 N/m)
The boundary conditions are shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Solution Type
SOL 101 — Linear Statics
Results
Type Point Bench Value NX Nastranσθθ (a, 0) 7.500E7 7.528E7σθθ (a, π/4) 2.500E7 2.511E7σθθ (a, π/2) –2.500E7 –2.452E7
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLP02/89.
Uniformly Distributed Load on a Circular Plate
This test is a linear statics analysis (three-dimensional problem) of a circular plate fixed at the edgewith transverse bending and a uniform load. It provides the input data and results for benchmark testSSLS03/89 from Guide de validation des progiciels de calcul de structures.
Test Case Data and Information
Input Files
• ssls03a.dat linear quadrilateral
• ssls03b.dat linear triangle
Units
SI
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
Finite Element Modeling
Test 1
• 38 linear quadrilateral thin shell (CQUAD4) elements
• 50 grid points
Test 2
• 53 linear triangular thin shell (CTRIA3) elements
• 38 grid points
Meshing is only done on 1/4 of the plate.
The meshes are shown in the following figure:
NX Nastran 11 Verification Manual 6-25
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Clamp free edges.
• Uniform pressure p = –1000 Pa.
• Symmetric conditions are applied to the sides.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result Grid Point Point Bench Value Test Number NX NastranZ 1.000 Center O –0.006500 1 –0.006600w (m) 1.000 2 –0.006500
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS03/89.
Torque Loading on a Square Tube
This test is a linear statics analysis (three-dimensional problem) of a thin-walled tube loaded in torsionby pure shear at the free end. It provides the input data and results for benchmark test SSLS05/89from Guide de validation des progiciels de calcul de structures.
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input File
ssls05.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• = 0.3
Finite Element Modeling
• 160 CQUAD4 elements
• 219 grid points
The mesh is shown in the following figure:
NX Nastran 11 Verification Manual 6-27
Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Plane X = 0
• Clamped beam
• Apply a torque equal to 10 Nm on the free end.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result Grid Point Bench Value NX NastranDisp. Y (m) 193.0 –6.170E–7 .6.170E–7Disp. Rx (rad) 1.230E–5 1.230E–5Stress XY Shear (Pa) –11.00E4 –11.00E4Disp. Y (m) 208.0 –9.870E–7 –9.870E–7Disp. Rx (rad) 1.970E–5 1.970E–5Stress XY Shear (Pa) –11.00E4 –11.00E4
Results are post-processed using the Shell surface: Bottom option.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS05/89.
Cylindrical Shell with Internal Pressure
This test is a linear statics analysis of a thin cylinder loaded by internal pressure. It provides theinput data and results for benchmark test SSLS06/89 from Guide de validation des progiciels decalcul de structures.
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Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input Files
• ssls06a.dat
• ssls06b.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
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Verification Test Cases from the Societe Francaise des Mecaniciens
Chapter 6: Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
The meshes are shown in the following figure:
Test 1
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
Test 2
• 400 liinear quadrilateral thin shell (CQUAD4) elements
• 441 grid points
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Free conditions:
To set free boundary conditions, use symmetry about XZ, XY, and YZ planes.
• Internal pressure = 10000 Pa.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Point Bench Value TestNumber
NX Nastran
σ11(Pa) All 0 1 1.7202 4.960
σ22(Pa) 5.000E5 1 4.950E52 4.990E5
ΔR(m) 2.380E–6 1 2.370E–62 2.380E–6
ΔL(m) –1.430E–6 1 –1.420E–62 –1.430E–6
All results are averages.
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Post Processing
• σ11 is the stress of z at grid point 11 (test 1) and grid point 21 (test 2)
• σ22 is the stress of x at grid point 111 (test 1) and grid point 421 (test 2)
• ΔR(m) is the displacement of x at grid point 121 (test 1) and grid point 441 (test 2)
• ΔL(m) is the displacement of z at grid point 121 (test 1) and grid point 441 (test 2)
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS06/89.
Uniform Axial Load on a Thin Wall Cylinder
This test is a linear static analysis of a thin cylinder loaded axially. It provides the input data andresults for benchmark test SSLS07/89 from Guide de validation des progiciels de calcul de structures.
Test Case Data and Information
Input Files
• ssls07a.dat – parabolic quadrilateral, thin shell
• ssls07b.dat – parabolic triangle, thin shell
Units
SI
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Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
Finite Element Modeling
Test 1
• 200 parabolic quadrilateral thin shell (CQUAD8) elements
• 661 grid points
Test 2
• 400 parabolic triangular thin shell (CTRIA6) elements
The meshes are shown in the following figure:
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Boundary Conditions
• Axial displacement = 0 in. X = 0 section
• Uniform axial load q = 10000 N/m
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Sstatics
Results
Type Point Bench Value Test Number NX Nastranσ11(Pa) Any 5.000E5 1 5.000E5
2 5.790E5σ22(Pa) Any 0 1 0
2 3.080E4ΔL(m) Any 9.520E–6 1 9.520E–6
2 9.560E–6ΔR (m) Any –7.140E–7 1 –7.140E-7
2 –7.330E–7
All results are averages.
Post Processing
• σ11 is the stress of z at grid point 641 in coordinate system 2.
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Verification Test Cases from the Societe Francaise des Mecaniciens
• σ22 is the stress of y at grid point 641 in coordinate system 2.
• ΔR is the displacement of x at grid point 641 in coordinate system 2.
• ΔL is the displacement of z at grid point 641 in coordinate system 2.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS07/89.
Hydrostatic Pressure on a Thin Wall Cylinder
This test is a linear statics analysis of a thin cylinder loaded by hydrostatic pressure. It provides theinput data and results for benchmark test SSLS08/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input File
ssls08.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
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Finite Element Modeling
• 200 parabolic quadrilateral thin shell (CQUAD8) elements
• 661 grid points
The mesh is shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Restrain the grid points on side A (from grid point 21 to grid point 661) in the X translation andthe Y and Z rotations.
• Restrain the grid points on side B (from grid point 1 to grid point 641) in the Y translation and Xand Z rotations.
• Internal pressure p = p0 * Z/L with p0 = 20000 Pa.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Grid Point Point Bench Value NX Nastranσ11(Pa) 321.0 Any 0 8.800E3L/2σ22 (Pa) 321.0 x = L/2 5.000E5 4.970E5ΔR (m) 321.0 x = L/2 2.380E–6 2.380E–6ΔL (m) 1.000 x = L –2.860E–6 2.860E–6Ψ (rad) 321.0 1.190E–6 1.190E–6
Ψ represents the rotation of a generator.
Post Processing
• σ11is the stress of z at grid point 321 in coordinate system 2
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• σ22 is the stress of y at grid point 321 in coordinate system 2
• ΔR is the displacement of x at grid point 321 in coordinate system 2
• ΔL is the displacement of z at grid point 1 in coordinate system 2
• Ψ is the rotation of y at grid point 321 in coordinate system 2
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS08/89.
Pinched Cylindrical Shell
This test is a linear statics analysis of a cylindrical shell with grid point forces, F, pinching as shown.It provides the input data and results for benchmark test SSLS20/89 from Guide de validation desprogiciels de calcul de structures.
Test Case Data and Information
Input Files
• ssls20a.dat linear triangle thin shells
• ssls20b.dat linear quadrilateral thin shells
Units
SI
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Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 10.5 x 106 Pa
• ν = 0.3125
Finite Element Modeling
Test 1
• 296 linear triangular thin shell (CTRIA3) elements
• 173 grid points
Test 2
• 140 linear quadrilateral thin shell (CQUAD4) elements
• 165 grid points
The meshes are shown in the following figure:
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Boundary Conditions
• Free conditions
To set free boundary conditions, use symmetry about XY, XZ, and YZ planes.
• Grid point forces Fy = –25 N at point D
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Type Point Bench Value Test Number NX NastranDisp. Y (Grid point 3) ν(m) D –113.9E-3 1 –114.4E–3Disp. Y (Grid point 3) 2 –113.3E–3
Post Processing
• ν(m) is the displacement of y at grid point 3 (quadrilateral).
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS020/89.
Spherical Shell with a Hole
This test is a linear statics analysis of a spherical shell with a hole with grid point forces. It providesthe input data and results for benchmark test SSLS21/89 from Guide de validation des progiciels decalcul de structures.
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Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input Files
• ssls21a.dat – linear quadrilateral thing shells
• ssls21b.dat – linear triangle thin shells
• ssls21c – parabolic quadrilateral thin shells
Units
SI
Material Properties
• E = 6.285 x 107 Pa
• ν = 0.3
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Finite Element Modeling
Test 1
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
Test 2
• 200 linear triangular thin shell (CTRIA3) elements
• 121 grid points
Test 3
• 100 parabolic quadrilateral thin shell (CQUAD8) elements
• 441 grid points
The mesh is shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Free conditions
To set free boundary conditions, use symmetry about XY and YZ planes.
• Grid point forces F = 2 Newtons
Due to the symmetric boundary conditions, only half of the load is applied.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result Point BenchValue
TestNumber
NX Nastran
u (m) grid point 111 A(R,0,0) 9.400E–2 1 102.0E–3Grid point 111 2 102.1E–3Grid point 421 3 100.9E–3
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS021/89.
Bending Load on a Cylindrical Shell
This test is a linear statics analysis of a cylindrical shell with bending and membrane effect. Itprovides the input data and results for benchmark test SSLS23/89 from Guide de validation desprogiciels de calcul de structures.
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Test Case Data and Information
Input Files
• ssls23a.dat (Test 1, linear)
• ssls23b.dat (Test 2, parabolic)
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
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Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
Test 1
• 60 linear quadrilateral thin shell (CQUAD4) elements
• 78 grid points
Test 2
• 60 parabolic quadrilateral thin shell (CQUAD8) elements
• 215 grid points
The mesh is shown in the following figure:
Boundary Conditions
• AB side: Clamped in local system coordinates.
• AD and BC sides: Restrain Z translation, θx and θy.
• DC side: Set bending moment CZ to 1000 Nm/m. Set in plane force to 0.6E6 N/m.
• ABCD surface: Set internal pressure to 0.6E06 N/m**2.
• AD and DC sides are restrained in the global coordinate system.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
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Results
Use coordinate system 3 (the cylindrical coordinate system) to display the results.
Results are post-processed using the Shell surface middle option.
Result Point Bench Value Test Number NX NastranGrid point 35 E 60.00 MPa 1 60.70Grid point 93 2 59.60
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS023/89.
Uniformly Distributed Load on a Simply-Supported Rectangular Plate
This test is a linear statics analysis of a plate with pressure loading and simple supports. It providesthe input data and results for benchmark test SSLS24/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input Files
• ssls24a.dat (Test 1, coarse mesh)
• ssls24b.dat (Test 2, fine mesh)
• ssls24c.dat (Test 3, very fine mesh)
Units
SI
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Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 1.0 x 107 Pa
• ν = 0.3
Finite Element Modeling
Test 1 — a/b = 1
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
Test 2 — a/b = 2
• 200 linear quadrilateral thin shell (CQUAD4) elements
• 231 grid points
Test 3 — a/b = 5
• 500 linear quadrilateral thin shell (CQUAD4) elements
• 561 grid points
The mesh is shown in the following figure:
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Boundary Conditions
Restraints
• All edges: w = 0
• One corner fixed
Loads
• Set pressure = 1 N/m**2 in the –Z direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Result a/b Parameters Bench Value Test Number NX Nastran61z direction 1.000 1.000α 0.004440 1 0.004500116z direction 2.000 2.000α 0.01110 2 0.01110281z direction 5.000 5.000α 0.01417 3 0.0140661x component topsurface
1.000 1.000β 2874. 1 2867.
116x component topsurface
2.000 2.000β 6102. 2 6034.
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Verification Test Cases from the Societe Francaise des Mecaniciens
Result a/b Parameters Bench Value Test Number NX Nastran281x component topsurface
5.000 5.000β 7476. 3 7331.
Where:
q = distributed load
b = dimension
t = thickness
E = elastic modules
β values of reference from the Guide de Validation are incorrect. The correct values are extractedfrom Formulas for Stress and Strain (Roark/Young).
Note
Note that the shell top surface corresponds to the side of the plate with negative globalZ coordinates.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS024/89.
Uniformly Distributed Load on a Simply-Supported Rhomboid Plate
This test is a linear statics analysis (three-dimensional problem) of a plate with pressure andtransverse bending. It provides the input data and results for benchmark test SSLS25/89 from Guidede validation des progiciels de calcul de structures.
• Thickness = 0.01 m
• b = 1.0 m
• a = 2.0 m
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Test Case Data and Information
Input Files
• ssls25a.dat (Test 1)
• ssls25b.dat (Test 2)
Units
SI
Material Properties
• E = 36.0 x 106 Pa
• ν = 0.3
Finite Element Modeling
• a/b = 2
• Linear quadratic thin shell (CQUAD4) elements
Test 1
• θ = 30°
Test 2
• θ = 45°
The mesh is shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• All edges: w = 0, one corner fixed
• Pressure = 1 N/m2 in the –Z direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Parameter Test Case Bench Value NX Nastranα Test 1
ssls25a
z displacement
–3.277E–3 m
116z displacement
–2.963E–3 mβ Y stress
–5.700E3 N/m2
116y stress
–5.831E3 N/m2α Test 2
ssls25b
z displacement
–3.000E-3 m
116z displacement
–2.720E–3 mβ Y stress
–5.390E3 N/m2
116Y stress
–5.441E3 N/m2
Where:
q = distributed load
b = dimension
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t = thickness
E = elastic modulus
Values of reference from the Guide de validation are incorrect. The correct values are extracted fromFormulas for Stress and Strain (Roark/Young), table 26, case number 14a.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS025/89.
Shear Loading on a Plate
This test is a linear statics analysis of a thin plate with torque and shear loading. It provides theinput data and results for benchmark test SSLS27/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input Files
• ssls27a.dat (Test 1, Mindlin)
• ssls27b.dat (Test 2, Kirchoff)
• ssls27c.dat (Test 3, Mindlin)
Units
SI
Material Properties
• E = 1.0 x 107 Pa
• ν = 0.25
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Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
Test 1 — Mindlin
• 6 linear quadrilateral thin shell (CQUAD4) elements
• 14 grid points
Test 2 — Kirchhoff
• 6 linear quadrilateral thin shell (CQUAD4) elements
• 14 grid points
Test 3 — Mindlin
• 48 linear quadrilateral thin shell (CQUAD4) elements
• 75 grid points
The meshes are shown in the following figure:
All tests are executed with mapped meshing
Boundary Conditions
• Clamp AD side
• Point B: grid point force Fz = –1N
• Point C: grid point force –Fz = 1N
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
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Results at Location C
Displacement at Gridpoint
Bench Value Test Number NX Nastran
14.00 3.537E–2 1 3.585E–214.00 3.537E–2 2 3.573E–275.00 3.537E–2 3 3.603E–2
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLS027/89.
Mechanical Structures — Linear Statics Analysis with Solid Elements
Solid Cylinder in Pure Tension
This test is a linear statics analysis of a solid cylinder with tension-compression. It provides theinput data and results for benchmark test SSLV01/89 from Guide de validation des progiciels decalcul de structures.
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Verification Test Cases from the Societe Francaise des Mecaniciens
Test Case Data and Information
Input Files
• sslv01a.dat (Test 1)
• sslv01b.dat (Test 2)
• sslv01c.dat (Test 3)
• sslv01d.dat (Test 4)
• sslv01e.dat (Test 5)
• sslv01f.dat (Test 6)
Units
SI
Material Properties
• E = 2.0 x 1011 Pa
• ν = 0.30
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Finite Element Modeling
Test 1
• 155 parabolic tetrahedron (CTETRA) elements
• 342 grid points
Test 2
• 144 linear brick (CHEXA) elements & 48 linear solid wedge (CPENTA) elements
• 307 grid points
Test 3 (Results for this test will be provided in the NX Nastran 7 Verification Manual)
• 48 linear quadrilateral axisymmetric solid elements
• 65 grid points
Test 4 (Results for this test will be provided in the NX Nastran 7 Verification Manual)
• 96 linear triangular axisymmetric solid elements
• 65 grid points
Test 5 (Results for this test will be provided in the NX Nastran 7 Verification Manual)
• 18 parabolic quadrilateral axisymmetric solid elements
• 95 grid points
Test 6
• 864 linear pyramid (CPYRAM) elements created by dividing each brick element in test 2 into 6pyramid elements. 48 linear wedge (CPENTA) elements remain.
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Verification Test Cases from the Societe Francaise des Mecaniciens
The meshes are shown in the following figure:
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Boundary Conditions
• Uniaxial deformation of the cylinder section
• Set uniformly distributed force –F/A on the free end in the Z direction
• F/A = 100 MPa
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
linear statics
* axisymmetric data will be provided in version 7
Point GridPoint
Displacement BenchValue
TestNumber
NX Nastran
A & C 6 u (m) 1.500E–3 1 1.500E–3A & C 279 2 1.500E–3A & C 1 3 *A & C 4 4 *A & C 1 5 *
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Point GridPoint
Displacement BenchValue
TestNumber
NX Nastran
A & C 279 6 1.500E–3B 4 u (m) 1.500E–3 1 1.500E–3B 307 2 1.500E–3B 53 3 *B 3 4 *B 39 5 *B 307 6 1.500E–3D 37 u (m) 1.000E-3 1 1.000E–3D 189 2 1.000E–3D 5 3 *D 25 4 *D 7 5 *D 189 6 1.000E–3E 41 u (m) 0.5000E-3 1 0.500E–3E 99 2 0.500E–3E 9 3 *E 29 4 *E 13 5 *E 99 6 0.500E–3A & C 6 w (m) –0.1500E–3 1 –0.150E–3A & C 279 2 –0.150E–3A & C 1 3 *A & C 4 4 *A & C 1 5 *A & C 279 6 –0.1500E–3D 37 w (m) –0.1500E-3 1 –0.1500E–3D 189 2 –0.1500E–3D 5 3 *D 25 4 *D 7 5 *D 189 6 –0.1500E–3E 41 w (m) –0.1500E–3 1 –0.1500E–3E 99 2 –0.1500E–3E 9 3 *E 29 4 *E 13 5 *
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Point GridPoint
Displacement BenchValue
TestNumber
NX Nastran
E 99 6 –0.1500E–3
Post Processing
To view the results for Test 1 and Test 2, use coordinate system 2 (cylindrical). u is the radialdisplacement and w is the axial displacement.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLV01/89.
Internal Pressure on a Thick-Walled Spherical Container
This test is a linear statics analysis of a thick sphere with internal pressure. It provides the input dataand results for benchmark test SSLV03/89 from Guide de validation des progiciels de calcul destructures.
Test Case Data and Information
Input Files
• sslv03a.dat (Test 1)
• sslv03b.dat (Test 2)
• sslv03c.dat (Test 3)
• sslv03d.dat (Test 4)
• sslv03e.dat (Test 5)
• sslv03f.dat (Test 6)
Units
SI
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Verification Test Cases from the Societe Francaise des Mecaniciens
Material Properties
• E = 2 x 105 Pa
• ν = 0.3
Finite Element Modeling
Test 1
• 1600 linear brick (CHEXA) elements & linear solid wedge (CPENTA) elements
• 1898 grid points
Test 2
• 200 parabolic brick (CHEXA) elements & 50 solid wedge (CPENTA) elements
• 1256 grid points
Test 3 (Results for this test will be provided in the NX Nastran 7 Verification Manual)
• 400 linear quadrilateral axisymmetric solid elements
• 451 grid points
Test 4 (Results for this test will be provided in the NX Nastran 7 Verification Manual)
• 400 parabolic quadrilateral axisymmetric solid elements
• 1301 grid points
Test 5
• Linear pyramid (CPYRAM) elements created by dividing each brick element in test 1 into 6pyramid elements. Wedge (CPENTA) elements remain.
Test 6
• Parabolic pyramid (CPYRAM) elements created by dividing each brick element in test 2 into 6pyramid elements. Wedge (CPENTA) elements remain.
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The meshes from these tests are shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• The equivalent of the center of the sphere being fixed is modeled via symmetric boundaryconditions.
• Uniform radial pressure = 100 MPa.
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
* axisymmetric data will be provided in version 7
Point GridPoint
DisplacementStress
BenchValue
Test Number NX Nastran
r=1 m 1 σrr (MPa) –100.0 1 –90.151 2 –97.29451 3 *451 4 *1 5 –90.841 6 -103.81 σθ (MPa) 71.43 1 72.09
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Point GridPoint
DisplacementStress
BenchValue
Test Number NX Nastran
1 2 77.23451 3 *451 4 *1 5 72.061 6 73.301 u (m) 0.4000E–3 1 0.4000E–31 2 0.4000E–3451 3 *451 4 *1 5 0.3991E–31 6 0.4006E–3
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Point GridPoint
DisplacementStress
BenchValue
Test Number NX Nastran
r=2 m 1826 σrr (MPa) 0 1 –0.02802221 2 0.2240411 3 *411 4 *1826 5 –0.25302221 6 –0.52591826 σθ (MPa) 21.43 1 21.182221 2 21.18411 3 *411 4 *1826 5 21.402221 6 21.741826 u (m) 1.500E–4 1 1.500E–42221 2 1.500E–4411 3 *411 4 *1826 5 1.506E–42221 6 1.499E–4
All stress results are averaged. Use the spherical coordinate system for the stress results.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLV03/89.
Internal Pressure on a Thick-Walled Infinite Cylinder
This test is a linear statics analysis of a thick cylinder with internal pressure. It provides the inputdata and results for benchmark test SSLV04/89 from Guide de validation des progiciels de calcul destructures.
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Test Case Data and Information
Input Files
• sslv04a.dat (Test 1)
• sslv04b.dat (Test 2)
• sslv04c.dat (Test 3)
• sslv04d.dat (Test 4)
• sslv04e.dat (Test 5)
• sslv04f.dat (Test 6)
Units
SI
Material Properties
• E = 2 x 105 mPa
• ν = 0.3
Finite Element Modeling
Test 1
• 400 linear brick (CHEXA) elements
• 902 grid points
Test 2
• 240 parabolic brick (CHEXA) elements
• 1873 grid points
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Test 3
• 600 linear quadrilateral axisymmetric solid elements
• 656 grid points
Test 4
• 600 parabolic quadrilateral axisymmetric solid elements
• 1911 grid points
Test 5
• Linear pyramid (CPYRAM) elements created by dividing each brick element in test 1 into 6pyramid elements.
Test 6
• Parabolic pyramid (CPYRAM) elements created by dividing each brick element in test 2 into6 pyramid elements.
The brick meshes are shown in the following figure:
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Boundary Conditions
• Unlimited cylinder
• Internal pressure p = 60 MPa
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
All results are averaged.
Test Case GridPoint
Displacement / Stress Bench Value NX Nastran
sslv04a 411 σr –60.00 (MPa) –57.00sslv04b 977 –60.00sslv04c 616 *sslv04d 1831 *sslv04e 411 –57.30sslv04f 977 –60.74sslv04a 411 σθ 100.0 (MPa) 99.70sslv04b 977 102.0sslv04c 616 *sslv04d 1831 *sslv04e 411 99.68sslv04f 977 100.9sslv04a 411 τmax 80.00 (MPa) 79.34sslv04b 977 81.00sslv04c 616 *sslv04d 1831 *
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Test Case GridPoint
Displacement / Stress Bench Value NX Nastran
sslv04e 411 80.82sslv04f 977 80.82sslv04a 411 ur 59.00E–6 (m) 59.00E–6sslv04b 977 59.00E–6sslv04c 616 *sslv04d 1831 *sslv04e 411 58.85E–6sslv04f 977 59.00E–6sslv04a 451 σr 0 (MPa) –0.006500sslv04b –0.04480sslv04c *sslv04d *sslv04e –0.1563sslv04f –0.1900sslv04a σθ 40.00 (MPa) 39.66sslv04b 40.39
sslv04c *sslv04d *sslv04e 39.84sslv04f 40.16
sslv04a τmax 20.00 (MPa) 20.08sslv04b 20.17sslv04c 20.07sslv04d 19.99sslv04e 20.10sslv04f 20.17sslv04a ur 40.00E–6 (m) 40.00E–6sslv04b 40.00E–6sslv04c *sslv04d *sslv04e 39.93E–6sslv04f 40.00E–6
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References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLV04/89.
Prismatic Rod in Pure Bending
This test is a linear statics analysis of a solid rod with bending. It provides the input data and resultsfor benchmark test SSLV08/89 from Guide de validation des progiciels de calcul de structures.
Test Case Data and Information
Input Files
• sslv08a.dat (Test 1)
• sslv08b.dat (Test 2)
• sslv08c.dat (Test 3)
• sslv08d.dat (Test 4)
• sslv08e.dat (Test 5)
• sslv08f.dat (Test 6)
Units
SI
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Material Properties
• E = 2 x 105 MPa
• ν = 0.3
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Finite Element Modeling
Test 1
• 198 linear solid tetrahedral (CTETRA) elements
• 76 grid points
Test 2
• 198 parabolic solid tetrahedral (CTETRA) elements
• 409 grid points
Test 3
• 48 linear brick (CHEXA) elements
• 117 grid points
Test 4 — Mapped meshing
• 48 parabolic brick (CHEXA) elements
• 381 grid points
Test 5
• 288 linear pyramid (CPYRAM) elements created by dividing each brick element in test 3 into6 pyramid elements.
Test 6
• 288 parabolic pyramid (CPYRAM) elements created by dividing each brick element in test 4 into6 pyramid elements.
The meshes from these tests are shown in the following figure:
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Boundary Conditions
• Clamp Point B.
• Other points of B section: Set Z-displacement to 0. NOTE: In these tests some grid points ofsection B are also restrained in the x direction about the x-axis at the free end of the rod.
• Set moment Mx equal to (4/3)E+7 N.m
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Test # Point GridPoint
DisplacementStress
Bench Value NX Nastran
1 F or G 5 σzz –10.00E6 (Pa) –4.268E62 5 –10.03E63 75 –10.00E64 245 –9.995E65 75 –7.929E66 245 –9.992E61 A 26 uA 4.000E–4 (m) 2.964E–42 90 4.000E–43 77 4.000E–44 251 4.000E–4
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Test # Point GridPoint
DisplacementStress
Bench Value NX Nastran
5 77 3.443E–46 251 4.000E–41 H 19 wB 2.000E–4 (m) 2.000E–42 40 2.000E–43 76 2.000E–44 249 2.000E–45 76 1.721E–46 249 2.000E–41 F or G 5 vF = -vG 0.1500E-4 (m) 0.07450E–42 5 0.1508E–43 75 0.1500E–44 245 0.1503E–45 75 0.1005E–46 245 0.1503E–41 D or E 8 vD = -vE -0.1500E-4 (m) –6.262E–42 8 –0.1505E–43 73 –0.1500E–44 241 –0.1503E–45 73 –0.1005E–46 241 –0.1503E–4
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLV08/89.
Thick Plate Clamped at Edges
This test is a linear statics analysis of a thick plate with pressure and transverse bending. It providesthe input data and results for benchmark test SSLV09/89 from Guide de validation des progiciels decalcul de structures.
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Test Case Data and Information
Input Files
• sslv09a.dat (Test 1)
• sslv09b.dat (Test 2)
• sslv09c.dat (Test 3)
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
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Finite Element Modeling
Test 1
• 25 parabolic linear brick (CHEXA) elements
• 228 grid points
• λ =10, 20, 50, 75, 100
Test 2
• 25 linear quadrilateral thin shell (CQUAD4) elements
• 36 grid points
• λ =10, 20, 50, 75, 100
Test 3
• 150 linear pyramid solid (CPYRAM) elements created by dividing each brick element in test1 into 6 pyramid elements
Test 2 is done using CQUAD4 elements with the thicknesses specified in the physical property table.
The meshes from these tests are shown in the following figure:
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Boundary Conditions
• AB and AD sides: clamped
• BC and DC sides: symmetry
• Load case 1:
Pressure p = 1E06 Pascals in –Z direction
• Load case 2: Point C
Grid Point force F = 1E06 N in –Z direction
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 Linear statics
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Results
Test Case 1 (z displacement at location C)
PartName
Load Case Grid Point Analytical Reference FEM NX Nastran
10 Pressure 242 –0.6552E-4 –0.7620E–4 –0.7379E–4
Force 242 –0.2915E-3 –0.4300E–3 –0.3684E–3
20 Pressure 1242 –0.5242E-3 –0.5383E–3 –0.5266E–3
Force 1242 –0.2332E–2 –0.2535E–2 –0.2456E–2
50 Pressure 2242 –0.8190E–2 –0.8029E–2 –0.7935E–2
Force 2242 –0.3643E–1 –0.3574E–1 –0.3602E–1
75 Pressure 3242 –0.2764E–1 –0.2690E–1 –0.2666E-1
Force 3242 –0.1230 –0.1184 –0.1206
100 Pressure 4242 –0.6552E–1 –0.6339E–1 –0.6305E–1
Force 4242 –0.2915 –0.2779 –0.2849
Test Case 2 (z displacement at location C)
PartName
Load Case Grid Point Analytical Reference FEM NX Nastran
10 Pressure 1 –0.6552E–4 –0.7866E–4 –0.8131E–4
Force 1 –0.2915E–3 –0.4109E–3 –0.4050E–3
20 Pressure 36 –0.5242E–3 –0.5557E–3 –0.5775E–3
Force 36 –0.2332E–2 –0.2595E–2 –0.2668E–2
50 Pressure 36 –0.8190E–2 –0.8348E–2 –0.8669E–2
Force 36 –0.3643E–1 –0.3745E–1 –0.3878E–1
75 Pressure 36 –0.2764E–1 –0.2805E–1 –0.2906E–1
Force 36 –0.1230 –0.1253 –0.1292
100 Pressure 36 –0.6552E–1 –0.6639E–1 –0.6864E–1
Force 36 –0.2915 -0.2958 –0.3042
Test Case 3 (z displacement at location C)
PartName
Load Case Grid Point Analytical Reference FEM NX Nastran
10 Pressure 242 –0.6552E-4 –0.7620E–4 –0.7491E–4
Force 242 –0.2915E-3 –0.4300E–3 –0.3736E–3
20 Pressure 1242 –0.5242E-3 –0.5383E–3 –0.5342E–3
Force 1242 –0.2332E–2 –0.2535E–2 –0.2458E–2
50 Pressure 2242 –0.8190E–2 –0.8029E–2 –0.7875E–2
Force 2242 –0.3643E–1 –0.3574E–1 –0.3470E–1
75 Pressure 3242 –0.2764E–1 –0.2690E–1 –0.2605E-1
Force 3242 –0.1230 –0.1184 –0.1135
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PartName
Load Case Grid Point Analytical Reference FEM NX Nastran
100 Pressure 4242 –0.6552E–1 –0.6339E–1 –0.6068E–1
Force 4242 –0.2915 –0.2779 –0.2627
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SSLV09/89.
Mechanical Structures — Normal Mode Dynamics Analysis
Lumped Mass-Spring System
This test is a normal mode dynamics analysis of an elastic link with lumped mass. It provides theinput data and results for benchmark test SDLD02/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input File
sdld02.dat
Units
SI
Material Properties
Spring constant
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Finite Element Modeling
• 8 lumped mass (CONM2) elements
• 9 spring (CBUSH) elements
• 8 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Clamp points A and B
• Other points:
ν = 0 ; θ = 0
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
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Results
Frequency Results (Hz)
Normal Mode Bench Value NX Nastran1 5.527 5.5272 10.89 10.893 15.92 15.924 20.46 20.465 24.38 24.386 27.57 27.577 29.91 29.918 31.35 31.35
Mode Shapes Results
The mode shapes results are exact. The multiplication coefficient is 3.162.
Normal Mode Point Bench Value NX Nastran1 P1 0.1612 0.05100
P2 0.3030 0.09580P3 0.4082 0.1291P4 0.4642 0.1468P5 0.4642 0.1468P6 0.4082 0.1291P7 0.3030 0.09580P8 0.1612 0.05100
8 P1 0.1612 0.05100P2 –0.3030 –0.09580P3 0.4082 0.1291P4 –0.4642 –0.1468P5 0.4642 0.1468P6 –0.4082 –0.1291P7 0.3030 0.09580P8 –0.1612 –0.05100
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLD02/89, p. 178.
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Short Beam on Simple Supports
This test is a modal analysis of a straight short beam with simple supports both inline and offset. Itprovides the input data and results for benchmark test SDLL01/89 from Guide de validation desprogiciels de calcul de structures.
Test Case Data and Information
Input Files
• sdll01a.dat (Test 1)
• sdll01b.dat (Test 2)
Units
SI
Material Properties
• E = 2 x 101111 Pa
• ν = 0.3
• ρ = 7800 kg/m3
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Finite Element Modeling
• 10 linear beam (CBAR) elements
• 11 grid points
The meshes are shown in the following figure:
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Boundary Conditions
Problem 1
• Point A (grid point 1): Constrain in all directions, except the Z rotation.
• Point B (grid point 2): Constrain in the Y and Z translations and X and Y rotations.
• All other grid points (3-11): Constrain in the Z translation and X and Y rotations.
• No load case.
Problem 2
• Point C (grid point 1): Constrain in all directions, except the Z rotation.
• Point D (grid point 2): Constrain in the Y and Z translations and X and Y rotations.
• All other grid points (3-11): Constrain in the Z translation and X and Y rotations.
• No load case.
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
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Results
Problem 1: Frequency results (Hz)
Normal Mode Bench Value NX NastranBending 1 431.6 437.2Tension 1 1266. 1265.Bending 2 1498. 1539.Bending 3 2871. 2925.Tension 2 3798. 3763.Bending 4 4378. 4328.
Problem 2: Frequency results (Hz)
Mode Number Bench Value NX Nastran1 392.8 398.52 902.2 927.33 1592. 1666.4 2629. 2815.5 3126. 3266.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL01/89.
Axial Loading on a Rod
This test is a modal analysis of a simply-supported beam with stress stiffening. It provides the inputdata and results for benchmark test SDLL05/89 from Guide de validation des progiciels de calcul destructures.
Test Case Data and Information
Input Files
• sdll05a.dat
• sdll05b.dat
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Units
SI
Material Properties
• E = 2 x 1011 Pa
• ρ = 7800 kg/m3
Finite Element Modeling
• 10 linear beam (CBAR) elements
• 11 grid points
The mesh is shown in the following figure:
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Boundary Conditions
• Points A: u = v = 0
• Points B: v = 0
• Load case 2 (grid point 2): Fx = 1E05N in –X direction
• Stress stiffening on
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Load Case Normal Mode Bench Value NX Nastran1 Bending 1 28.70 28.68
Bending 2 114.8 114.42 Bending 1 22.43 22.40
Bending 2 109.1 108.7
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL05/89.
Cantilever Beam with a Variable Rectangular Section
This test is a modal analysis of a straight cantilever beam with a variable section. It provides theinput data and results for benchmark test SDLL09/89 from Guide de validation des progiciels decalcul de structures.
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Test Case Data and Information
Input Files
• sdll09a.dat
• sdll09b.dat
Units
SI
Material Properties
• E = 2 x 1011 Pa
• ρ = 7800 kg/m3
Finite Element Modeling
• 10 tapered beam (CBEAM) elements
• 11 grid points
The mesh is shown in the following figure:
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Boundary Conditions
• Clamp point A
• No load case
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
β Normal Mode Bench Value NX Nastran4 1 54.18 54.24
2 171.9 172.43 384.4 384.94 697.2 695.45 1112. 1104.
5 1 56.55 56.592 175.8 176.33 389.0 389.54 702.4 700.65 1118. 1109.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL09/89.
Thin Circular Ring
This test is a modal analysis of a thin curved beam. It provides the input data and results forbenchmark test SDLL11/89 from Guide de validation des progiciels de calcul de structures.
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Test Case Data and Information
Input File
sdll11.dat
Units
SI
Material Properties
• E = 7.2 x 1010 Pa
• ν = 0.3
• ρ = 2700 kg/m3
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Finite Element Modeling
• 36 linear beam (CBAR) elements
• 36 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Free conditions
• Create one constraint set (kinematic DOF) to fully constrain the three grid points shown below(grid points 7, 21, 30).
• No load case
The boundary conditions are shown in the following figure:
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Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran ADS #Plane mode 1,2,3 0 0 1.000, 2.000, 3.000Plane mode 4,5 318.4 319.0 7.000, 8.000Plane mode 6,7 900.5 900.9 11.00, 12.00Plane mode 8,9 1727. 1724. 15.00, 16.00Plane mode 10,11 2792. 2781. 17.00, 18.00Transverse Mode1,2,3
0 0 4.000, 5.000, 6.000
Transverse Mode 4,5 511.0 511.0 9.000, 10.00Transverse Mode 6,7 1590. 1585. 13.00, 14.00Transverse Mode 8,9 3184. 3159. 19.00, 20.00
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL11/89.
Thin Circular Ring Clamped at Two Points
This test is a modal analysis of a thin curved beam. It provides the input data and results forbenchmark test SDLL12/89 from Guide de validation des progiciels de calcul de structures.
Test Case Data and Information
Input File
sdll12.dat
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Units
SI
Material Properties
• E = 7.2 x 1010 Pa
• ν = 0.3
• ρ = 2700 kg/m3
Finite Element Modeling
• 29 linear beam (CBAR) elements
• 29 grid points
The mesh is shown in the following figure:
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Boundary Conditions
• Points A and B: Clamped in local coordinate system
• No load case
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 235.3 235.92 575.3 575.23 1106. 1103.4 1406. 1399.5 1751. 1743.6 2557. 2536.7 2802. 2723.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL12/89.
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Vibration Modes of a Thin Pipe Elbow
This test is a modal analysis of a straight cantilever beam, and a thin curved beam. It provides theinput data and results for benchmark test SDLL14/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input Files
• sdll14a.dat (test 1, L=0)
• sdll14b.dat (test 2, L=0.6)
• sdll14c.dat (test 3, L=2.0)
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg/m3
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Finite Element Modeling
• L = 0 or L = 0.6:
18 linear beam (CBAR) elements
19 grid points
• L = 2:
28 linear beam (CBAR) elements
29 grid points
Two of the meshes are shown in the following figure:
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Boundary Conditions
• Clamp points C and D
• Point A: v = 0; w = 0
• Point B: u = 0; w = 0
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
L Normal Mode Bench Value NX Nastran ADS#0 Transverse 1 44.23 44.07 1.000
Plane 1 119.0 119.2 2.000Transverse 2 125.0 125.4 3.000Plane 2 227.0 225.0 4.000
0.6000 Transverse 1 33.40 33.15 1.000Plane 1 94.00 94.42 2.000Transverse 2 100.0 98.50 3.000Plane 2 180.0 183.7 4.000
2.000 Transverse 1 17.90 17.65 1.000Plane 1 24.80 24.40 3.000Transverse 2 25.30 24.94 2.000
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L Normal Mode Bench Value NX Nastran ADS#Plane 2 27.00 26.67 4.000
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL14/89.
Cantilever Beam with Eccentric Lumped Mass
This test is a modal analysis of a straight cantilever beam and a lumped mass. It provides the inputdata and results for benchmark test SDLL15/89 from Guide de validation des progiciels de calcul destructures.
Test Case Data and Information
Input Files
• sdll15a.dat
• sdll15b.dat
Units
SI
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Material Properties
• E = 2.1 x 1011 Pa
• ρ = 7800 kg/m3
Finite Element Modeling
Test 1:
• 10 linear beam (CBEAM) elements
• 1 rigid (RBAR) element from point B to point C
• 1 lumped mass (CONM2) element at point C
• 11 grid points
Test 2:
• 10 linear beam (CBAR) elements
• 1 rigid (RBAR) element from point B to point C
• 1 lumped mass (CONM2) element at point C
• 11 grid points
The mesh both tests is is shown in the following figure:
Boundary Conditions
• Clamp point A
The boundary conditions are shown in the following figure:
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Solution Type
SOL 103 normal mode dynamics — SVI
Results
Frequency results (Hz)
yc Normal Mode Bench Value NX Nastran0 Transverse 1,2 1.650 1.650
Transverse 3,4 16.07 15.88Transverse 5,6 50.02 48.64Tension 1 76.47 76.42Torsion 1 80.47 80.68Transverse 7,8 103.2 97.89
1 1 1.636 1.6332 1.642 1.6383 13.46 13.364 13.59 13.595 28.90 29.206 31.96 31.577 61.61 59.858 63.93 61.72
Mode shapes results
yc Normal Mode Modal Displacement Bench Value NX Nastran1 1 wc/wb 1.030 1.030
2 uc/vb 0.1480 –0.14803 uc/vb 2.882 –2.9044 wc/wb –0.9220 –0.9800
• wc = z displacement at point C
• wb = z displacement at point B
• uc = x displacement at point C
• vb = y displacement at point B
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL15/89.
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Verification Test Cases from the Societe Francaise des Mecaniciens
Thin Square Plate (Clamped or Free)
This test is a normal mode dynamics analysis (three-dimensional problem) of a thin plate. It providesthe input data and results for benchmark test SDLS01/89 from Guide de validation des progiciels decalcul de structures.
Test Case Data and Information
Input Files
• sdls01a.dat
• sdls01b.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg/m3
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Finite Element Modeling
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Problem 1: AB side clamped
• Problem 2: Free plate; 1 kinematic DOF set (grid points 1, 11, 111)
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
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Results
Problem 1: Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 8.727 8.6382 21.30 20.893 53.55 52.424 68.30 65.775 77.74 75.146 136.0 127.8
Problem 2: Frequency results (Hz)
Normal Mode Bench Value NX Nastran7 33.71 32.918 49.46 47.429 61.05 59.1910,11 87.52 83.08
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLS01/89..
Simply-Supported Rectangular Plate
This test is a normal mode dynamics analysis (three-dimensional problem) of a thin plate. It providesthe input data and results for benchmark test SDLS03/89 from Guide de validation des progiciels decalcul de structures.
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Test Case Data and Information
Input Files
sdls03.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg/m3
Finite Element Modeling
• 150 linear quadrilateral thin shell (CQUAD4) elements
• 176 grid points
The mesh is shown in the following figure:
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Verification Test Cases from the Societe Francaise des Mecaniciens
Boundary Conditions
• Z-displacement = 0 on all sides of the plate
• One DOF set
• No load case
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Mode Dynamics
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 35.63 35.272 68.51 67.293 109.6 108.54 123.3 120.85 142.5 138.26 197.3 188.2
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLS03/89.
Thin Ring Plate Clamped on a Hub
This test is a normal mode dynamics analysis (three-dimensional problem) of a thin plate. It providesthe input data and results for benchmark test SDLS04/89 from Guide de validation des progiciels decalcul de structures.
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• Re = 0.1 m
• Ri = 0.2 m
• Thickness = .001 m
Test Case Data and Information
Input Files
sdls04.dat
Units
SI
Material Properties
• E = 2 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg/m3
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Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 400 linear quadrilateral thin shell (CQUAD4) elements
• 440 grid points
The mesh is shown in the following figure:
Boundary Conditions
• If r = Ri: Clamp in local coordinate system.
• No load case.
The boundary conditions are shown in the following figure:
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Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 79.26 79.222,3 81.09 80.724,5 89.63 88.836,7 112.8 111.38,9 Not available 152.710,11 Not available 212.912,13 Not available 290.114,15 Not available 382.916,17 Not available 490.318 518.9 510.919,20 528.6 519.721,22 559.1 546.223 609.7 590.3
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLS04/89.
Vane of a Compressor - Clamped-free Thin Shell
This test is a normal mode dynamics analysis (three-dimensional problem) of a cylindrical thin shell.It provides the input data and results for benchmark test SDLS05/89 from Guide de validation desprogiciels de calcul de structures.
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• α = 0.5 rad
• AD = L = 0.3048m
• r = 2L = 0.6096m
• thickness = 3.048 x 10–3 m
Test Case Data and Information
Input Files
• sdls05a.dat (coarse mesh)
• sdls05b.dat (fine mesh)
Units
SI
Material Properties
• E = 2.0685 x 1011 Pa
• ν = 0.3
• ρ = 7857.2 kg/m3
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Finite Element Modeling — Coarse Mesh
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
The coarse mesh is shown in the following figure:
Finite Element Modeling — Fine Mesh
• 225 linear quadrilateral thin shell (CQUAD4) elements
• 256 grid points
The fine mesh is shown in the following figure:
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Boundary Conditions
• AD side: Clamped in local coordinate system.
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran coarsemesh
NX Nastran fine mesh
1 85.60 84.60 85.302 134.5 137.1 137.83 259.0 240.7 243.94 351.0 333.3 338.15 395.0 370.0 378.36 531.0 503.7 515.4
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLS05/89.
Bending of a Symmetric Truss
This test is a normal mode dynamics analysis (plane problem) of a straight cantilever beam structure.It provides the input data and results for benchmark test SDLX01/89 from Guide de validation desprogiciels de calcul de structures.
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• h = 0.0048 m
• b = 0.029 m
• A = 1.392 x 10–4 m2
• Iz = 2.673 x 10–10 m4
Test Case Data and Information
Input File
sdlx01.dat
Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg/m3
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Verification Test Cases from the Societe Francaise des Mecaniciens
Finite Element Modeling
• 24 linear beam (CBAR) elements
• 24 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Clamp points A and B
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Modes
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Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 8.800 8.7692 29.40 29.343 43.80 43.824 56.30 56.255 96.20 95.436 102.6 102.57 147.1 146.28 174.8 173.19 178.8 177.410 206.0 202.911 266.4 262.412 320.0 309.713 335.0 321.9
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLX01/89.
Hovgaard's Problem — Pipes with Flexible Elbows
This test is a normal mode dynamics analysis (three-dimensional problem) of a straight cantileverbeam structure. It provides the input data and results for benchmark test SDLX02/89 from Guide devalidation des progiciels de calcul de structures.
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Verification Test Cases from the Societe Francaise des Mecaniciens
• A = 0.3439 x 10E–2 m2
• R = 0.922 m
• e = 0.00612 m
• Re = 0.0925 m
• Ri = 0.08638 m
• Iy = Iz = 0.1377x10–4 m4 (straight elements)
• Iy = Iz = 0.5887x10–5 m4 (curved elements)
Test Case Data and Information
Input Files
sdlx02.dat
Units
SI
Material Properties
• E = 1.658 x 1011 Pa
• ν = 0.3
• ρ = 13404.106 kg/m3
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Finite Element Modeling
• 25 linear beam (CBAR) elements
• 26 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Clamp points A and B
The boundary conditions are shown in the following figure:
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Solution Type
SOL 103 — Normal Modes
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 10.18 10.392 19.54 19.853 25.47 25.324 48.09 47.745 52.86 51.786 75.94 83.007 80.11 85.128 122.3 125.89 123.2 127.7
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLX02/89.
Rectangular Plates
This test is a normal mode dynamics analysis (three dimensional problem) of a thin plate with rigidbody modes. It provides the input data and results for benchmark test SDLX03/89 from Guide devalidation des progiciels de calcul de structures.
Test Case Data and Information
Input Files
sdlx03.dat
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Units
SI
Material Properties
• E = 2.1 x 1011 Pa
• ν = 0.3
• ρ = 7800 kg / m3
Finite Element Modeling
• 300 linear quadrilateral thin shell (CQUAD4) elements
• 320 grid points
The mesh is shown in the following figure:
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Boundary Conditions
• Free plate
• One DOF set
The boundary conditions are shown in the following figure:
Solution Type
SOL 103 — Normal Mode Dynamics
Results
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 584.0 577.02 826.0 813.03 855.0 844.04 911.0 895.05 1113. 1062.6 1136. 1118.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLX03/89.
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Mechanical Structures — Normal Mode Dynamics Analysis andModel Response
Transient Response of a Spring-Mass System with Acceleration Loading
This test is an undamped transient response by modal superposition. It provides the input data andresults for benchmark test SDLD04/89 from Guide de validation des progiciels de calcul de structures.
Where:
• m = 1 kg
• k = 1000 N/m
Test Case Data and Information
Input Files
sdld04.dat
Units
SI
Material Properties
Spring constant.
Finite Element Modeling
• 3 lumped mass (CONM) elements
• 3 translational spring (CELAS) elements
The mesh is shown in the following figure:
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Boundary Conditions
• Points A: Clamped (u = v = 0 : θ - 0)
• Points B, C and D: v = 0 ; = 0
• Point A: Set acceleration: ű(t) = 2E5 * (t2) ; (0 < t < 0.1 s)
• Initial condition: u(0) = 0 ; u(0) = 0 at every point
The mesh and the boundary conditions are shown in the following figure:
Solution Type
SOL 112 — Modal Transient Response
Results
The mode shapes results are exact.
Frequency results (Hz)
Normal Mode Bench Value NX Nastran1 2.239 2.2392 6.275 6.2753 9.069 9.069
Mode shapes results
Normal Mode Point Bench Value NX Nastran1 B 0.4450 0.4450
C 0.8019 0.8019D 1.000 1.000
2 B 1.000 1.000C 0.4450 0.4450D –0.8019 –0.8019B –0.8019 –0.8019C 1.000 1.000D –0.4450 –0.4450
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Transient response (Point D: X-displacement in meters)
Time (sec) Bench Value NX Nastran0.02000 –0.002700 –0.0026700.04000 –0.04260 –0.042700.05000 –0.1041 –0.10410.06000 –0.2158 –0.21600.08000 –0.6813 –0.68180.1000 –1.658 –1.659
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLD04/89.
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Transient Response of a Clamped-free Post
This test is a transient response of a straight cantilever beam with acceleration and force loadings,and modal damping. It provides the input data and results for benchmark test SDLL06/89 from "Guidede validation des progiciels de calcul de structures."
Test Case Data and Information
Input Files
sdll06.dat
Units
SI
Material Properties
• E = 4 x 1010 Pa
• Iz = 3.285 x 10–1 m4
• ρ = 0
Finite Element Modeling
• 8 linear beam (CBAR) elements
• 9 grid points
The mesh is shown in the following figure:
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Boundary Conditions
To apply an acceleration üA(t) at point A, we can do the following:
• Points A: Clamped (u = v = 0 : θ - 0)
• Point B: Set nodal force Fx(t) equal to mB * üA(t) in the -X direction
Fx(t) = –m * üA(t)
• Initial conditions: u(0) = 0 ; u (0) = 0 at every point
The mesh and the boundary conditions are shown in the following figure:
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Solution Type
SOL 109 — Direct Transient Response
Results
uB displacement (mm)
Time (s) Bench Value NX Nastran0.01000 –0.06500 –0.065700.02000 –0.5130 –0.51520.03000 –1.679 –1.6820.04000 –3.457 –3.4640.05000 –5.316 –5.3330.06000 –6.764 –6.8040.07000 –7.609 –7.6820.08000 –7.774 –7.8910.09000 –7.244 –7.4130.1000 –6.068 –6.2890.1200 –2.242 –2.5420.1400 2.367 2.0700.1600 6.149 5.9770.1800 7.783 7.8470.2000 6.698 7.042
The problem with damping is not computed.
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References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. SDLL06/89.
Stationary Thermal Tests — Heat Transfer Analysis
Hollow Cylinder - Fixed Temperatures
This test is a steady-state heat transfer analysis of a 2D axisymmetric cylinder with fixedtemperatures. It provides the input data and results for benchmark test TPLA01/89 from "Guide devalidation des progiciels de calcul de structures."
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• Re = 0.30 m
• Ri = 0.35 m
Test Case Data and Information
Input Files
htpla01.dat
Units
SI
Material Properties
• λ = 1 W/m °C
Finite Element Modeling
• 5 linear axisymmetric solid CQUADX4 elements and 5 parabolic axisymmetric solid CQUADX8elements
• 10 linear axisymmetric solid CTRAX3 elements and 10 parabolic axisymmetric solid CTRAX6elements
The triangular element mesh is shown in the following figure:
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Boundary Conditions
• One temperature set:
– Internal temperature Ti = 100 °C
– External temperature Te = 20 °C
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature results
Radius (m) Bench Value(°C)
NX Nastran(°C)
CTRAX3
NX Nastran(°C)
CTRAX6
NX Nastran(°C)
CQUADX4
NX Nastran(°C)
CQUADX80.3000 100.0 100.0 100.0 100.0 100.00.3100 82.98 82.98 82.98 82.98 82.980.3200 66.51 66.51 66.51 66.51 66.510.3300 50.54 50.54 50.54 50.54 50.540.3400 35.04 35.04 35.04 35.04 35.040.3500 20.00 20.00 20.00 20.00 20.00
Flux results
Radius (m) Bench Value(W/m2)
NX Nastran(W/m2)CTRAX3
NX Nastran(W/m2)CTRAX6
NX Nastran(W/m2)
CQUADX4
NX Nastran(W/m2)
CQUADX80.3000 1730. 1702. 1711. 1702. 1702.0.3100 1674. 1675. 1674. 1675. 1675.0.3200 1622. 1622. 1622. 1622. 1622.0.3300 1573. 1573. 1573. 1573. 1573.0.3400 1526. 1527. 1527. 1527. 1527.0.3500 1483. 1505. 1497. 1504. 1504.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLA01/89.
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Hollow Cylinder - Convection
This test is a steady-state heat transfer analysis of a 2D axisymmetric cylinder with convection. Itprovides the input data and results for benchmark test TPLA03/89 from "Guide de validation desprogiciels de calcul de structures."
• Re = 0.300 m
• Ri = 0.391 m
Test Case Data and Information
Input Files
htpla03.dat
Units
SI
Material Properties
• λ = 40.0 W/m °C
Finite Element Modeling
• 11 linear axisymmetric solid CQUADX4 elements and 1 parabolic axisymmetric solid CQUADX8element
• 22 linear axisymmetric solid CTRAX3 elements and 2 parabolic axisymmetric solid CTRAX6elements
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The triangular element mesh is shown in the following figure:
Boundary Conditions
• Convection on internal surface:
hi = 150.0 W/m2 / °C
Ti = 500 °C
• Convection on external surface:
he = 142.0 W/m2 / °C
Ti = 20 °C
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature/ Flux Bench Value NX Nastran
CTRAX3NX NastranCTRAX6
NX NastranCQUADX4
NX NastranCQUADX8
Ti (°C) 272.3 272.2 272.4 272.5 272.4Te (°C) 205.1 204.6 204.5 204.6 204.5φi (W/m2) 3.416E4 3.20E4 3.11E4 1.56E4 2.98E4φe (W/m2) 2.628E4 2.77E4 2.85E4 1.56E4 2.98E4
φ / l = φ * 2 * π * R
So: φ / l= 34173.82 * 2 * π * 0.300 = 64416.13 W/m
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLA03/89.
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Cylindrical Rod - Flux Density
This test is a steady-state heat transfer analysis of a 2D axisymmetric rod with fixed temperaturesand flux density. It provides the input data and results for benchmark test TPLA05/89 from "Guide devalidation des progiciels de calcul de structures."
Test Case Data and Information
Input Files
htpla05.dat
Units
SI
Material Properties
• λ = 33.33 W/m °C
Finite Element Modeling
• 40 linear axisymmetric solid CTRAX3 elements
• 20 linear axisymmetric solid CQUADX4 elements
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The quadrilateral element mesh is shown in the following figure:
Boundary Conditions
• z = 0
Set temperature to 0 °C
• z = 1
Set temperature to 500 °C
• Cylindrical surface
Set flux to –200 W/m2
The boundary conditions are shown in the following figure:
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Solution Type
SOL 153 — Steady State Heat transfer
Temperature results (°C)
Grid Point # z (m) Bench value NX Nastran(CTRAX3)
NX Nastran(CQUADX4)
Grid point 3 0.0000 0.000 0.000 0.000Grid point 41 0.1000 -4.000 -4.020 -4.020Grid point 39 0.2000 4.000 3.980 3.980Grid point 37 0.3000 24.00 23.97 23.97Grid point 35 0.4000 56.00 55.97 55.97Grid point 33 0.5000 100.0 99.97 99.97Grid point 31 0.6000 156.0 156.0 156.0Grid point 29 0.7000 224.0 224.0 224.0Grid point 27 0.8000 304.0 304.0 304.0Grid point 25 0.9000 396.0 396.0 396.0Grid point 4 1.000 500.0 500.0 500.0
Results are post-processed on the internal surface. NX Nastran does not make the approximation, T= cte when r is fixed.
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLA05/89.
Hollow Cylinder with Two Materials - Convection
This test is a steady-state heat transfer analysis of a 2D axisymmetric cylinder with two materialsand convection. It provides the input data and results for benchmark test TPLA08/89 from "Guide devalidation des progiciels de calcul de structures."
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• Ri = 0.30 m
• Rm = 0.35 m
• Re = 0.37 m
Test Case Data and Information
Input Files
htpla08.dat
Units
SI
Material Properties
• Material 1: λ1 = 40.0 W/m °C
• Material 2: λ2 = 20.0 W/m °C
Finite Element Modeling
• 14 linear axisymmetric solid CTRAX3 elements
• 7 linear axisymmetric solid CQUADX4 elements
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The triangular element mesh is shown in the following figure:
Boundary Conditions
• Convection on internal surface
hi = 150.0 W/m2 °C
Ti = 70 °C
• Convection on external surface
he = 200.0 W/m2 °C
Te = –15 °C
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Grid point # TemperatureFlux
Bench Value NX Nastran(CTRAX3)
NX Nastran(CQUADX4)
Grid point 9 Ti (°C) 25.42 25.45 25.45Grid point 14 Tm (°C) 17.69 17.68 17.68Grid point 16 Te (°C) 12.11 12.09 12.11Grid point 9 φi (W/m2) 6687. 6609. 6558.Grid point 14 φm (W/m2) 5732. 5768. 5733.Grid point 16 φe (W/m2) 5422. 5497. 5497.
φ/l = φ * 2 * π * R
So: φ/l= 5733.33 * 2 * π * 0.35 = 12608.25 W/m
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References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLA08/89.
Wall-Convection
This test is a steady-state heat transfer analysis of a 1D wall with fixed convection. It provides theinput data and results for benchmark test TPLL03/89 from "Guide de validation des progiciels decalcul de structures."
Test Case Data and Information
Input Files
htpl03.dat
Units
SI
Material Properties
• λ = 1.0 W/m °C
Finite Element Modeling
• 1 linear quadrilateral thin shell (CQUAD4) element
• 4 grid points
The thin shell element thickness is set to 1 m.
The mesh is shown in the following figure:
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Boundary Conditions
• Convection on internal surface
hA = 20.0 W/m2 °C
TA = –20.0 °C
• Convection on external surface
hB = 10.0 W/m2 °C
TB = 500.0 °C
• Convection coefficient is defined as
energy / (length * time * temperature) in the current system of units.
The boundary conditions are shown in the following figure:
Solution Type
SOL 153 — Steady State Heat Transfer
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Results
Temperature results (°C)
Grid point # Temperature/Flux Bench Value NX NastranGrid point 2 TA (°C) 21.71 21.71Grid point 4 TB (°C) 416.6 416.6Grid point 1 (W/m2) 834.2 834.3
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLL03/89.
Wall-Fixed Temperatures
This test is a steady-state heat transfer analysis of a 1D wall with fixed temperatures. It provides theinput data and results for benchmark test TPLL01/89 from "Guide de validation des progiciels decalcul de structures."
Test Case Data and Information
The mesh is shown in the following figure:
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Input Files
htpl01.dat
Units
SI
Material Properties
• λ = 0.75 W/m °C
Finite Element Modeling
• 5 linear beam (CBAR) elements
• 6 grid points
Boundary Conditions
• Internal temperature Ti = 100 °C
• External temperature Te = 20 °C
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature results (°C)
Grid point # Length: x (m) Bench Value NX NastranGrid point 1 0 100.0 100.0Grid point 3 0.01000 84.00 84.00Grid point 4 0.02000 68.00 68.00Grid point 5 0.03000 52.00 52.00Grid point 6 0.04000 36.00 36.00Grid point 2 0.05000 20.00 20.00
The flux calculated with NX Nastran is exact:
= 1200 Ω / μ2
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No. TPLL01/89.
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L-Plate
This test is a steady-state heat transfer analysis of a 2D L-plate with fixed temperatures. It providesthe input data and results for benchmark test TPLP01/89 from "Guide de validation des progiciels decalcul de structures."
Test Case Data and Information
Input Files
htpp01a.dat - linear quadrilateral thin shell elements
htpp01b.dat - parabolic quadrilateral thin shell elements
Units
SI
Material Properties
• λ = 1.0 W/m °C
Finite Element Modeling
• Test 1 – 12 linear quadrilateral thin shell (CQUAD4) elements
• Test 2 – 12 parabolic quadrilateral thin shell (CQUAD8) elements
The mesh is shown in the following figure:
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Boundary Conditions
• AF side
Set temperature to 10 °C
• DE side
Set temperature to 0 °C
Solution Type
SOL153 — Steady State Heat Transfer
Results
Temperature Results (°C)
Node Bench Value NX Nastran CQUAD4 NX Nastran CQUAD88 7.869 7.924 7.8829 5.495 5.613 5.519
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Node Bench Value NX Nastran CQUAD4 NX Nastran CQUAD810 2.816 2.885 2.83419 8.018 8.043 8.01518 5.680 5.821 5.66520 2.881 2.963 2.87717 8.514 8.425 8.5186 6.667 6.667 6.66716 2.972 3.148 2.96221 9.001 8.992 9.10715 8.640 8.356 8.66814 9.316 9.189 9.2825 9.009 8.773 8.961
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.TPLP01/89.
Orthotropic Square
This test is a steady-state heat transfer analysis of a square plate with orthotropic conduction andconvection. It provides the input data and results for benchmark test TPLP02/89 from "Guide devalidation des progiciels de calcul de structures."
Test Case Data and Information
Input Files
htpp02.dat
Units
SI
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Material Properties
• λx = 1.00 W/m °C
• λx =.75 W/m °C
Finite Element Modeling
• 100 linear quadrilateral thin shell (CQUAD4) elements
• 121 grid points
The thin shell element thickness is set to 1 m.
The mesh is shown in the following figure:
Boundary Conditions
• Flux density y = 60 W/m2 for face y = –0.1. (Entry)
• Flux density y = –60 W/m2 for face y = 0.1. (Exit)
• Convection on the faces X = –0.1 and x = 0.1:
– h = 15.0 W/m2 °C
• Linear variation of the external temperatures:
– Te = 30 – 80y on the face x = –0.1
– Te = 15 – 80y on the face x = 0.1
• Convection coefficient is defined as:
– Energy / (length * time * temperature)
• Flux density is defined as:
– Energy / (length * time) in the current system of units
The boundary conditions are shown in the following figure:
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Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature Results
Point Bench Value (°C) NX Nastran (°C)0 22.50 22.50A 35.00 34.80B 26.00 25.80C 10.00 10.20D 19.00 19.20
E 30.50 30.50F 18.00 18.00G 14.50 14.50H 27.00 27.00
Flux Results (W/m2)
Grid Point Bench Value NX Nastran
61 X 45.00 45.0061 Y 60.00 59.55
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References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.TPLP02/89.
Hollow Sphere - Fixed Temperatures, Convection
This test is a steady-state heat transfer analysis of a 3D sphere with fixed temperatures andconvection. It provides the input data and results for benchmark test TPLV02/89 from "Guide devalidation des progiciels de calcul de structures."
• Ri = 0.30 m
• Re = 0.35 m
Test Case Data and Information
Input Files
htpv02.dat (CHEXA and CPENTA)
htpv02p.dat (CPYRAM and CPENTA)
Units
SI
Material Properties
• λ = 1 W/m °C
Finite Element Modeling
Test 1: Brick and wedge element test
• 500 linear brick (CHEXA) and linear wedge (CPENTA) elements
• 766 grid points
The test is executed on 1/8 mapped meshed sphere.
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The mesh is shown in the following figure:
Test 2: Pyramid and wedge element test
• Linear pyramid (CPYRAM) elements created by dividing each brick element in test 1 into 6pyramid elements. Linear wedge (CPENTA) elements remain.
Boundary Conditions
• Convection on internal surface
hi = 30 W/m2 °C
Ti = 100 °C
• Set external surface temperature Te to 20 °C
The load sets are shown in the following figure:
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Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature results (°C)
Test Radius r (m) Bench Value NX NastranTest 1 0.3000 65.00 64.88Test 2 0.3000 65.00 64.86Test 1 0.3100 54.84 54.75Test 2 0.3100 54.84 54.72Test 1 0.3200 45.31 45.25Test 2 0.3200 45.31 45.23Test 1 0.3300 36.36 36.33Test 2 0.3300 36.36 36.30Test 1 0.3400 27.94 27.92Test 2 0.3400 27.94 27.91Test 1 0.3500 20.00 20.00Test 2 0.3500 20.00 20.00
Flux results (W/m 2): (X-direction)
Test Radius r (m) Bench Value NX NastranTest 1 0.3000 1050. 1013.Test 2 0.3000 1050. 1013.Test 1 0.3100 983.4 981.4Test 2 0.3100 983.4 981.6Test 1 0.3200 922.9 921.2Test 2 0.3200 922.9 921.3Test 1 0.3300 867.5 866.3
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Test Radius r (m) Bench Value NX NastranTest 2 0.3300 867.5 866.3Test 1 0.3400 817.5 816.3Test 2 0.3400 817.5 816.1Test 1 0.3500 771.4 792.4Test 2 0.3500 771.4 792.1
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.TPLV02/89.
Hollow Sphere with Two Materials - Convection
This test is a steady-state heat transfer analysis of a 3D sphere with two materials and convection.It provides the input data and results for benchmark test TPLV04/89 from "Guide de validation desprogiciels de calcul de structures."
• Ri = 0.30 m
• Rm = 0.35 m
• Re = 0.37 m
Test Case Data and Information
Input Files
htpv04a.dat (CHEXA and CPENTA elements)
htpv04b.dat (CTETRA elements)
htpv04c.dat (CTRAX6 elements)
htpv04p.dat (CPYRAM and CPENTA elements)
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Units
SI
Material Properties
• Material 1: λ1 = 40.0 W/m °C
• Material 2: λ2 = 20.0 W/m °C
Finite Element Modeling
• Test 1 - 700 linear brick (CHEXA) and linear wedge (CPENTA) elements
• Test 2 - 2192 parabolic tetrahedron (CTETRA) elements
• Test 3 - 8 parabolic axisymmetric (CTRAX6) elements
• Test 4- Linear pyramid (CPYRAM) elements created by dividing each brick element in test 1 into6 pyramid elements. Linear wedge (CPENTA) elements remain.
The test is executed on a 1/8 meshed sphere
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The meshes are shown in the following figure:
Boundary Conditions
• Convection on internal surface:
hi = 150.0 W/m2 °C
Ti = 70 °C
• Convection on external surface:
he = 200.0 W/m2 °C
Te = –9 °C
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The boundary conditions are shown in the following figure:
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature Results
Temperature/ Flux
BenchValue
CHEXA &CPENTA
CTETRA CTRAX6 CPYRAM &CPENTA
Ti (°C) 25.06 N1 25.02 N19 25.06 24.98 N1 23.66Tm (°C) 17.84 N556 17.84 N9 17.84 17.72 N556 16.26Te (°C) 13.16 N778 13.18 N5 13.15 13.17 N778 13.85φi (W/m2) 6741. N1 6487. N19 5865. 6390. N1 6683.φm (W/m2) 4952. N556 4931. N9 4765. 4819. N556 5080.φe (W/m2) 4431. N778 4531. N5 4551. 4508. N778 4669.
φ = φ * 4 * π * R2
So: φ = 4931.20 * 4 * π * 0.352 = 7590.00 W
Flux is in the x direction
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.TPLV04/89.
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Thermo-mechanical Tests — Linear Statics Analysis
Orthotropic Cube
This test is a steady-state heat transfer analysis of a 3D cube with convection and flux density. Itprovides the input data and results for benchmark test TPLV07/89 from "Guide de validation desprogiciels de calcul de structures."
Test Case Data and Information
Input Files
htpv07.dat (CHEXA)
htpv07p.dat (CPYRAM)
Units
SI
Material Properties
• λx = 1.00 W/m °C
• λy = 0.75 W/m °C
• λz = 0.50 W/m °C
Finite Element Modeling
Test 1: Brick element test
• 512 linear brick (CHEXA) elements
• 729 grid points
The mesh is shown in the following figure:
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Test 2: Pyramid element test
• 3072 linear pyramid (CPYRAM) elements created by dividing each brick element in test 1 into6 pyramid elements.
Boundary Conditions
• Flux density y = 60 W/m2 for face y = –0.1 (Entry)
• Flux density y = –60 W/m2 for face y = 0.1 (Exit)
• Flux density z = 30 W/m2 for face z = –0.1 (Entry)
• Flux density z = –30 W/m2 for face z = 0.1 (Exit)
• Convection on the faces X = –0.1 and x = 0.1:
–h = 15.0 W/m2 °C
• Linear variation of the external temperatures:
–Te = 30 – 80y – 60z on the face x = –0.1
–Te = 15 – 80y – 60z on the face x = 0.1
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The boundary conditions are shown in the following figure:
Solution Type
SOL 153 — Steady State Heat Transfer
Results
Temperature results (°C)
Test Point Bench Value NX NastranTest1 A 35.00 34.70Test2 A 35.00 34.70Test1 B 26.00 25.70Test2 B 26.00 25.70Test1 C 10.00 10.30Test2 C 10.00 10.30Test1 D 19.00 19.30Test2 D 19.00 19.30Test1 S 30.50 30.40Test2 S 30.50 30.40Test1 F 18.00 18.00Test2 F 18.00 18.00Test1 M 14.50 14.60Test2 M 14.50 17.70Test1 H 27.00 27.00Test2 H 27.00 27.00
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Test Point Bench Value NX NastranTest1 N 29.00 29.00Test2 N 29.00 29.00Test1 P 20.00 20.00Test2 P 20.00 20.00Test1 J 4.000 4.600Test2 J 4.000 4.590Test1 I 13.00 13.60Test2 I 13.00 13.60Test1 E 16.50 16.60Test2 E 16.50 16.60Test1 R 41.00 40.40Test2 R 41.00 40.40Test1 Q 32.00 31.40Test2 Q 32.00 31.40Test1 K 16.00 16.00Test2 K 16.00 16.00Test1 L 25.00 25.00Test2 L 25.00 25.00Test1 G 28.50 28.40Test2 G 28.50 28.40
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.TPLV07/89.
Thermal Gradient on a Thin Pipe
This test is a thermo-mechanical linear statics analysis of a thin pipe with thermal gradient andplane strain. It provides the input data and results for benchmark test HSLA01/89 from "Guide devalidation des progiciels de calcul de structures."
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• Ri = 0.020 m
• Re = 0.025 m
Test Case Data and Information
Input Files
hsla01.dat
Units
SI
Material Properties
• E = 1.0 x 1011 Pa
• ν = 0.3
• Coefficient of expansion: α = 1.0 x 10–5/°C
Finite Element Modeling
• 1000 linear axisymmetric solid (CTRAX3) elements
• 500 linear axisymmetric solid (CQUADX4) elements
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The quadrilateral element mesh is shown in the following figure:
Boundary Conditions
• Articulate AB side
• Radial temperature with Ti = 100 °C, and Te = 0 °C.
The boundary conditions are shown in the following figure:
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Solution Type
SOL 101 Linear statics
Results
Point Stress Bench Value(Pa)
NX Nastran(Pa)(CTRAX3)
NX Nastran(Pa)(CQUADX4)
r = Ri σr 0 –14.03E6 –0.848E6σθ –74.07E6 –79.84E6 –74.26E6
r = (Re + Ri) / 2 σr –3.950E6 –3.908E6 –3.890E6σθ 1.306E6 1.469E6 1.390E6
r = Re σr 0 –11.31E6 –0.649E6σθ 68.78E6 73.69E6 68.48E6
References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.HSLA01/89.
Simply-Supported Arch
This test is a thermo-mechanical linear statics analysis of a thin curved beam with thermal gradientand articulation. It provides the input data and results for benchmark test HSLL01/89 from "Guide devalidation des progiciels de calcul de structures."
• R = 10 m
• A = 144 x 10–4 m2
• I = 1.728 x 10–5 m4
Beam cross section:
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Test Case Data and Information
Input Files
hsll01.dat
Units
SI
Material Properties
• E = 0.2 x 1011 Pa
• = 0.3
• Coefficient of expansion: α = 11.0 x 10–6/C°
Finite Element Modeling
• 50 linear beam (CBAR) elements
• 51 grid points
The mesh is shown in the following figure:
Boundary Conditions
• Articulate point A and B
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• Top temperature Ts = 160 °C
• Middle temperature Tm = 100 °C
• Bottom temperature Ti = 40 °C
The boundary conditions are shown in the following figure:
Solution Type
SOL 101 — Linear Statics
Results
Point Force Moment Bench Value NX Nastranθ = π/2 M 0 4.040 e–5
N 0 15.10T –479.2 –527.6
θ = π/4 M 3388. 3729.N –338.8 –373.2T –338.8 –373.2
θ = 0 M 4792. 5277.N –479.2 527.5T 0 15.00
Post Processing
List the beam forces
• M - Z bending moment
• N - axial force
• T - Y shear force
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References
Societe Francaise des Mecaniciens. Guide de validation des progiciels de calcul de structures. Paris,Afnor Technique, 1990. Test No.HSLL01/89.
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Chapter 7: Material Nonlinear (Plasticity) VerificationUsing Standard NAFEMS Benchmarks
7.1 Overview of the Material Nonlinear (Plasticity) Verification UsingNAFEMS Test CasesThe purpose of this section is to verify the accuracy and robustness of NX Nastran. The plasticityverification uses test cases published by the National Agency for Finite Element Methods andStandards (NAFEMS) in Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. (See Reference.)
To perform the tests, input data is applied to single elements including plane strain elements,plane stress elements, axisymmetric solid elements, and solid elements. Results are tabulatedand compared to results published by NAFEMS.
The plasticity verification includes perfect plasticity and isotropic hardening tests. Within thesecategories, results for uniaxial, biaxial, and triaxial displacement tests are provided.
Understanding the Verification Format
The format for the nonlinear section of the Solver Verification document looks somewhat differentfrom the linear section. Each test case in this section provides a brief description of the test includinginput data. The results are then displayed in the form of a graph comparing NX Nastran Nonlinearresults published by NAFEMS for the same test case.
Reference
The following reference has been used in the NX Nastran Plasticity verification problems:
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987.
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Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Test Cases
Plane Strain Elements - Perfect Plasticity Tests
This article provides input data and results for perfect plasticity tests including prescribed uniaxial andprescribed biaxial displacement tests. The tests were run on these plane stress elements:
• Linear triangle (CTRIA3) elements
• Linear quadrilateral (CQUAD4) elements
The material description and initial boundary conditions are the same for the uniaxial and biaxialdisplacement tests.
Test Case Data and Information
Input Files
nlspls89.dat (uniaxial)
nlspls90.dat (biaxial)
Units
Inch
Attributes
Load Control
Material Properties
• E = 250000.0
• = 0.25
• σy = 5.0
• H = 0.0
• εo = 0.000025 (strain at first yield)
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Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
The following figure shows the plane strain elements and the boundary conditions applied toeach. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not illustrate the time history ofthe applied conditions.
NX Nastran 11 Verification Manual 7-3
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
The following graph shows results of the uniaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults compared with NAFEMS test results for plane strain with perfect plasticity.
History Strain XX Strain YY Strain ZZ1 0.2500D–4 0D+00 0D+002 0.5000D–4 0D+00 0D+003 0.2500D–4 0D+00 0D+004 0D+00 0D+00 0D+00
10 increments per strain history step
7-4 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results for plane strain with perfect plasticity.
History Stage Strain XX Strain YY Strain ZZ1 0.2500D–4 0D+00 0D–002 0.5000D–4 0D+00 0D–003 0.5000D–4 0.2500D–4 0D–004 0.5000D–4 0.5000D–4 0D–005 0.2500D–4 0.5000D–4 0D–006 0D+00 0.5000D–4 0D+007 0D+00 0.2500D–4 0D+008 0D+00 0D+00 0D+00
10 increments per strain history step
NX Nastran 11 Verification Manual 7-5
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.3-2.25.
Plane Strain Elements - Isotropic Hardening Tests
This article provides input data and results for isotropic hardening tests including prescribed uniaxialand prescribed biaxial displacement tests. The tests were run on these plane strain elements:
• Linear triangle (CTRIA3) elements
• Linear quadrilateral (CQUAD4) elements
The material description and initial boundary conditions are the same for the uniaxial and biaxialdisplacement tests.
Test Case Data and Information
Input Files
nlspls91.dat (uniaxial)
nlspls92.dat (biaxial)
Units
Inch
Attributes
Load Control
Material Properties
• E = 250000.0
• = 0.25
• σy = 5.0
• H = 62500.0
7-6 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
• εo = 0.000025 (strain at first yield)
Boundary Conditions
The following figure shows the plane strain elements and the boundary conditions applied toeach. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not illustrate the time history ofthe applied conditions.
NX Nastran 11 Verification Manual 7-7
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results for plane strain with isotropic hardening.
History Strain XX Strain YY Strain ZZ1 0.2500D–4 0D+00 0D+002 0.5000D–4 0D+00 0D+003 0.2500D–4 0D+00 0D+004 0D–00 0D+00 0D+00
10 increments per strain history step
7-8 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the uniaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test result for plane strain with isotropic hardening.
History Stage Strain XX Strain YY Strain ZZ1 0.2500D–4 0D+00 0D+002 0.5000D–4 0D+00 0D+003 0.5000D–4 0.2500D–4 0D+004 0.5000D–4 0.5000D–4 0D+005 0.2500D–4 0.5000D–4 0D+006 0D–00 0.5000D–4 0D+007 0D–00 0.2500D–4 0D+008 0D–00 0D–00 0D+00
10 increments per strain history step
NX Nastran 11 Verification Manual 7-9
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.26 - 2.35.
Plane Stress Elements - Perfect Plasticity Tests
This article provides input data and results for perfect plasticity tests including prescribed uniaxial andprescribed biaxial displacement tests. The tests were run on these plane strain elements:
• Linear triangle (CTRIA3) elements
• Linear quadrilateral (CQUAD4) elements
The material description and initial boundary conditions are the same for the uniaxial and biaxialdisplacement tests.
The following figure shows the geometry:
Test Case Data and Information
Input Files
nlspls61.dat (uniaxial test), linear quadrilateral (CQUAD4) elements
nlspls62.dat (uniaxial test), linear triangle (CTRIA3) elements
nlspls65.dat (biaxial test), linear quadrilateral (CQUAD4) elements
nlspls66.dat (biaxial test), linear triangle (CTRIA3) elements
Units
Inch
Material Properties
• E = 250000.0
• = 0.25
• σy = 5.0
7-10 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
• H = 0.0
• o = 0.2080126 x 10–4 (strain at first yield)
Boundary Conditions
The following figure shows the plane strain elements and the boundary conditions applied toeach. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not illustrate the time history ofthe applied conditions.
NX Nastran 11 Verification Manual 7-11
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
The following graph shows results of the uniaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results for plane stress with perfect plasticity.
History Strain XX Strain YY Strain ZZ1 0.2080D–4 0D+00 -0.6934D–52 0.4160D–4 0D+00 -0.2538D–43 0.2080D–4 0D+00 -0.1835D–44 0.4235D–21 0D+00 -0.1128D–4
10 increments per strain history step
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the plane strain elements.
7-12 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results.
History Stage Strain XX Strain YY Strain ZZ1 0.2080D–4 0D+00 -0.6934D–52 0.4160D–4 0D+00 -0.2528D–43 0.4160D–4 0.2080D–4 -0.4284D–44 0.4160D–4 0.4160D–4 -0.6513D–45 0D–00 0.4160D–4 -0.5035D–46 0D–00 0.1872D–4 -0.3871D–47 0D–00 0D–00 -0.1867D–4
10 increments per strain history step
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.36 - 2.47.
NX Nastran 11 Verification Manual 7-13
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Plane Stress Elements - Isotropic Hardening Tests
This article provides input data and results for isotropic hardening tests including prescribed uniaxialand prescribed biaxial displacement tests. The tests were run on the these plane stress elements:
• Linear triangle (CTRIA3) elements
• Linear quadrilateral (CQUAD4) elements
The material description and initial boundary conditions are the same for the uniaxial and biaxialdisplacement tests.
The following figure shows the geometry:
Test Case Data and Information
Input Files
nlspls71.dat (uniaxial test), linear quadrilateral (CQUAD4) elements
nlspls72.dat (uniaxial test), linear triangle (CTRIA3) elements
nlspls75.dat (biaxial test), linear quadrilateral (CQUAD4) elements
nlspls76.dat (biaxial test), linear triangle (CTRIA3) elements
Units
Inch
Material Properties
• E = 250000.0
• = 0.25
• σy = 5.0
• H = 62500.0
• o = 0.2080126 x 10–4 (strain at first yield)
7-14 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
The following figure shows the plane strain elements and the boundary conditions applied toeach. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not show the time history ofthe applied conditions.
NX Nastran 11 Verification Manual 7-15
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
The following graph shows results of the uniaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 0.2080D–4 0D+00 -0.6934D–52 0.4160D–4 0D+00 -0.2249D–43 0.2080D–4 0D+00 -0.1555D–44 0.4235D–21 0D+00 -0.8619D–5
10 increments per strain history step
7-16 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the plane strain elements.
Results are exactly the same for both elements. The graph shows the NX Nastran Nonlinear testresults (points) compared to NAFEMS test results.
History Stage Strain XX Strain YY Strain ZZ1 0.2080D–4 0D+00 -0.6934D–52 0.4160D–4 0D+00 -0.2249D–43 0.4160D–4 0.2080D–4 -0.3569D–44 0.4160D–4 0.4160D–4 -0.5406D–45 0.2080D–4 0.4160D–4 -0.4712D–46 0D–00 0.4160D–4 -0.4102D–47 0D–00 0.2080D–4 -0.3408D–48 0D–00 0D–00 -0.2715D–4
10 increments per strain history step
NX Nastran 11 Verification Manual 7-17
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.47 - 2.58.
Solid Element - Perfect Plasticity Tests
This article provides input data and results for perfect plasticity tests including prescribed uniaxial,biaxial, and triaxial displacement tests. The tests were run on the solid parabolic brick element.
Test Case Data and Information
Input Files
nlspls08.dat
Units
Inch
Material Properties
• E = 250000.0
• = 0.25
• y = 5.0
• H = 0.0
• o = 0.000025 (strain at first yield)
Boundary Conditions
The following figure shows the parabolic brick (CHEXA) element and the boundary conditions appliedto it. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not show the time history ofthe applied conditions.
7-18 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 2.500E–5 0E+00 0E+004 0E+00 0E+00 0E+00
10 increments per strain history step
NX Nastran 11 Verification Manual 7-19
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
The following graph shows results of the uniaxial displacement test for the solid brick element. Itshows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
7-20 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the solid brick element. Thegraph shows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 5.000E–5 2.500E–5 0E+004 5.000E–5 5.000E–5 0E+005 2.500E–5 5.000E–5 0E+006 0E+00 5.000E–5 0E+007 0E+00 2.500E–5 0E+008 0E+00 0E+00 0E+00
- 10 increments per strain history step
NX Nastran 11 Verification Manual 7-21
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Triaxial Displacement Test — Applied Strain History
The following graph shows results of the triaxial displacement test for the solid brick element. Thegraph shows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 5.000E–5 2.500E–5 0E+004 5.000E–5 5.000E–5 0E+005 5.000E–5 5.000E–5 2.500E–56 5.000E–5 5.000E–5 5.000E–57 2.500E–5 5.000E–5 5.000E–58 0E+00 5.000E–5 5.000E–59 0E+00 2.500E–5 5.000E–510 0E+00 0E+00 5.000E–511 0E+00 0E+00 2.500E– 512 0E+00 0E+00 0E+00
7-22 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
- 10 increments per strain history step
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.59-2.79.
Solid Element - Isotropic Hardening Tests
This article provides input data and results for isotropic hardening tests including prescribed uniaxial,biaxial, and triaxial displacement tests. The tests were run on the solid parabolic brick element(CHEXA), which has 20 grid points.
Test Case Data and Information
Input Files
nlspls09.dat
Units
Inch
Material Properties
• E = 250000.0
• = 0.25
• y = 5.0
• H = 62500.0
• o = 0.000025 (strain at first yield)
Boundary Conditions
The following figure shows the parabolic brick element and the boundary conditions applied toit. The strain state is completely defined as a function of time since all degrees of freedom aresuppressed or prescribed.
These boundary conditions represent initial conditions only and do not show the time history ofthe applied conditions.
NX Nastran 11 Verification Manual 7-23
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
7-24 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Results
Uniaxial Displacement Test — Applied Strain History
The following graph shows results of the uniaxial displacement test for the solid brick element. Itshows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 2.500E–5 0E+00 0E+004 0E+00 0E+00 0E+00
- 10 increments per strain history step
NX Nastran 11 Verification Manual 7-25
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Biaxial Displacement Test — Applied Strain History
The following graph shows results of the biaxial displacement test for the solid brick element. Thegraph shows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 5.000E–5 2.500E–5 0E+004 5.000E–5 5.000E–5 0E+005 2.500E–5 5.000E–5 0E+006 0E+00 5.000E–5 0E+007 0E+00 2.500E–5 0E+008 0E+00 0E+00 0E+00
- 10 increments per strain history step
7-26 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Triaxial Displacement Test — Applied Strain History
The following graph shows results of the triaxial displacement test for the solid brick element. Thegraph shows the NX Nastran Nonlinear test results (points) compared to NAFEMS test results.
History Strain XX Strain YY Strain ZZ1 2.500E–5 0E+00 0E+002 5.000E–5 0E+00 0E+003 5.000E–5 2.500E–5 0E+004 5.000E–5 5.000E–5 0E+005 5.000E–5 5.000E–5 2.500E–56 5.000E–5 5.000E–5 5.000E–57 2.500E–5 5.000E–5 5.000E–58 0E+00 5.000E–5 5.000E–59 0E+00 2.500E–5 5.000E–510 0E+00 0E+00 5.000E–511 0E+00 0E+00 2.500E–512 0E+00 0E+00 0E+00
NX Nastran 11 Verification Manual 7-27
Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
- 10 increments per strain history step
References
Hinton, E., and Ezatt, M.H. Fundamental Tests for Two and Three Dimensional, Small Strain,Elastoplastic Finite Element Analysis. East Kilbride, Glasgow, UK: National Agency for Finite ElementMethods and Standards, April, 1987 pp. 2.80-2.92.
7-28 NX Nastran 11 Verification Manual
Chapter 7: Material Nonlinear (Plasticity) Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification UsingStandard NAFEMS Benchmarks
8.1 Overview of the Geometric Nonlinear Verification UsingNAFEMS Test CasesThis section verifies the accuracy and robustness of the arc-length method of NX Nastran. Thegeometric nonlinear verification uses test cases published by the National Agency for Finite ElementMethods and Standards (NAFEMS) in NAFEMS Non-Linear Benchmarks and A Review of BenchmarkProblems for Geometric Non-linear Behaviour of 3-D Beams and Shells. (See References.)
Understanding the Verification Format
Each test case includes the following information.
• Test case data and information:
- Units
- Material properties
- Finite element modeling information
- Boundary conditions (loads and restraints)
- Solution type
• Results — time history versus Load Factor plots are presented. (Note that in NX Nastran, theload factor is displayed as "eigenvalue".)
• Reference
Reference
The following references have been used for these verification problems:
• NAFEMS Non-Linear Benchmarks. Glasgow: NAFEMS, Oct., 1989., Rev. 1. Test No. NL6.
• NAFEMS, A Review of Benchmark Problems for Geometric Non-Linear Behaviour of 3-D Beamsand Shells (Summary) (Glasgow: NAFEMS, Ref. R0024.)
NX Nastran 11 Verification Manual 8-1
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Test Cases
Straight Cantilever with End Moment
This test is a nonlinear analysis of a single row of equal-sized elements. This document provides theinput data and results for NAFEMS Non-linear Benchmarks NL5.
Test attributes:
• Bending action only
• Initially straight elements
• Load control
Test Case Data and Information
Input Files
nfnl05a.dat (load control)
nfnl05b.dat (arc-length control)
Units
SI
Material Properties
• E = 210 x 109 N / m2
• = 0.0
SI
Finite Element Modeling
32 linear beam (CBEAM) elements
8-2 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• U = V = = 0 at point B
• Concentrated load at Point A applied in equal increments up to a maximum value of M L / 2 πE I = 1.0
Solution Type
SOL 106 — Geometric Nonlinear
• Loading method — arc-length control.
• Adaptive search control:
– Initial increment factor = 0.05
– Target number of iterations = 6
– Maximum number of splits = 3
– Max increment factor = 1
– Number of reporting steps = 18
Geometric nonlinear 2
NX Nastran 11 Verification Manual 8-3
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Loading method — load control.
• 6 equal steps.
Results
Normalizing Constants
• 2 E I / L = 3436.12 x 103 Nm
• L = 3.2 m
• 2 = 6.28319
Graphs of Results
• Free end axial displacement vs. Load Factor
8-4 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Vertical displacement at grid point 33 vs. Load Factor
NX Nastran 11 Verification Manual 8-5
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Rotational displacement at grid point 33 vs. Load Factor
References
National Agency for Finite Element Methods and Standards, NAFEMS Non-Linear Benchmarks(Glasgow: NAFEMS, Oct., 1989., Rev. 1). Test No. NL5.
Straight Cantilever with Axial End Point Load - Brick Elements
This test is a nonlinear analysis of a straight cantilever with an axial end point load, made up of asingle row of straight elements. This document provides the input data and results for NAFEMSNon-linear Benchmarks NL6.
8-6 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Attributes of this test are:
• Combined bending and membrane action.
• Presence of bifurcation.
• Initially straight elements.
• Load control.
Test Case Data and Information
Input Files
nlsarg07.dat
Units
SI
Material Properties
• E = 210 x 109 N/m2
• = 0.0
NX Nastran 11 Verification Manual 8-7
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Finite Element Modeling
256 solid parabolic brick (CHEXA) elements.
Boundary Conditions
• U = V = θ = 0 at point B.
• Concentrated load at Point A applied in increments up to a value of PL2 / EI = 22.493.
Solution Type
SOL 106 — Geometric Nonlinear
Results
Normalizing Constants:
• EI / L2 = 170898 N
• L + 3.2 m
• = 3.14159
8-8 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Graphs of results:
• X-displacement at cantilever end point vs. Load Factor.
NX Nastran 11 Verification Manual 8-9
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Y-displacement at cantilever end point vs. Load Factor
Reference
National Agency for Finite Element Methods and Standards. NAFEMS Non-Linear Benchmarks.Glasgow: NAFEMS, Oct., 1989., Rev. 1. Test No. NL6.
8-10 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Straight Cantilever with Axial End Point Load - BEAM Elements
This test is a nonlinear analysis of a single row of straight elements. This document provides theinput data and results for NAFEMS Non-linear Benchmarks NF6.
Test Case Data and Information
Input Files
nlsarp01.dat
Units
SI
Material Properties
• E = 210 x 109 N/m2
• = 0.0
Finite Element Modeling
32 linear (CBEAM) elements
NX Nastran 11 Verification Manual 8-11
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• U = V = θ = 0 at point B.
• Concentrated load at Point A applied in increments up to a value of PL2 / EI = 22.493 or P =–3.85 x 106 N
Solution Type
SOL 106 — Geometric Nonlinear
Results
Normalizing Constants:
• EI / L 2 = 170898 N
• π = 3.14159
8-12 NX Nastran 11 Verification Manual
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Graphs of results:
• X-displacement at grid point 33 vs. Load Factor
NX Nastran 11 Verification Manual 8-13
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Y-displacement at grid point 33 vs. Load Factor
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Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
• Rz-displacement at grid point 33 vs. Load Factor
Reference
National Agency for Finite Element Methods and Standards, NAFEMS Non-Linear Benchmarks.Glasgow: NAFEMS, Oct., 1989., Rev. 1. Test No. NL6.
Lee's Frame Buckling Problem
This test is a nonlinear analysis of a single row of straight elements. This document provides theinput data and results for NAFEMS Non-linear Benchmarks NF7. Attributes of this test are:
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Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
nlsarg01.dat
Units
SI
Material Properties
• E = 71.74 x 109 N/m2
• = 0.0
Finite Element Modeling
20 linear beam (CBEAM) elements
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Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• U = V = 0; θ ≠ 0 at points B and C
• Concentrated load at Point A applied incrementally using arc-length constraint with automaticadjustment of arc length (P = –20000 N)
Solution Type
SOL 106 — Geometric Nonlinear
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Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Results
Normalizing Constants EI / L2 = 996.389 N, L = 1.2 m
Graphs of results: Y-displacement at grid point 13 vs. Load Factor
Reference
National Agency for Finite Element Methods and Standards. NAFEMS Non-Linear Benchmarks.Glasgow: NAFEMS, Oct., 1989., Rev. 1. Test No. NL7.
Large Displacement Elastic Response of a Hinged Spherical Shell UnderUniform Pressure Loading
This test is a nonlinear analysis of a hinged spherical shell element under uniform pressure loading.This document provides the input data and results for A Review of Benchmark Problems forGeometric Non-Linear Behaviour of 3-D Beams and Shells (Summary) 3DNLG-7.
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Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Test Case Data and Information
Input Files
nlsarg05.dat
Units
SI
Material Properties
• E = 69
• = 0.3
Finite Element Modeling
• The shell midsurface is defined in terms of the global Cartesian coordinate system where Z =2.0285 x 10 –4 [X (1570 – X) + Y (1570 – Y)].
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Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Boundary Conditions
• Evenly distributed follower pressure load normal to shell surface. Maximum pressure = 0.1.Pressure follows the deformation of the shell surface.
Solution Type
SOL 106 — Geometric Nonlinear
• Loading method:
o Arc-length control
• Adaptive search control:
o Initial increment factor = 0.3
o Target number of iterations = 6
o Maximum number of splits = 3
o Maximum increment factor = 1
o Number of reporting steps = 18
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Chapter 8: Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
Results
Magnitude displacement at grid point 145 vs. Load Factor
Reference
• National Agency for Finite Element Methods and Standards. A Review of Benchmark Problemsfor Geometric Non-Linear Behaviour of 3-D Beams and Shells (Summary) Glasgow: NAFEMS,Ref. R0024. Test No. 3DNLG-7
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Geometric Nonlinear Verification Using Standard NAFEMS Benchmarks
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