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2015
Jose Pardellas Bello & Marcos Benedí
European University of Madrid UEM
Aerospace Engineering in Aircrafts
Aerodynamic Airfoil – Wing Project
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INDEX
Introduction And Data
2D Analysis. Conclussions
3D Analysis. Conclussions
Comparisson 2D & 3D.
Final Conclussions
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Introduction to the Project And Relevant Data to be used:
The main objective of the project is to obtain acknowledgments on how an airfoil and a wing
behaves in experimental analysis process.
We have to take into consideration that the airfoil we have used is an airfoil that may not fit
real flight conditions; and that flight conditions that we have assume for each airfoil may not
be the correct ones to obtain real values for our profile; we assume a lot of flight conditions as
flight velocity; height at steady state; density of the fluid in where the airfoil is analyzed;
treated the fluid as air; and all assumptions it concerns relates to air flow model.
We have to know that the Root Chord measurements are 20 cm. and the span assumed to be
analyzed in 3D are 0,5m.
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ANALYSIS
We have to analyze an airfoil profile (2D) and an airfoil wing (3D).
ANALYSIS WITH XFLR 5 (2D)
1st we have to export our airfoil which we have created with EXCEL and a notepad page; taking
the measured points for our first airfoil profile; but after iterate our measured points with an
N-10 ideal profile with XFLR5; we obtain the airfoil profile which we going to operate during
the analysis (2D & 3D)
Airfoil Before Iteration; Green = N-10 & Red = Approach Airfoil Measures
Airfoil After Iteration & Airfoil taken for Ansys Analysis in 2D
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After interpolations, we obtain the next graph values:
Cl /Alpha Graph; we can see at 0 angle of attack we obtain a value near to 0,4 lift coefficient;
we have the Zero lift angle of attack near to -3.5
At 0 angle of attack, we obtain a Lift to Drag Coefficient ratio of 24
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3D ANALYSIS
To make the 3D analysis we will start setting up the Xflow menu; and import the NACA
geometry saved in .igs format
We will set the wind tunnel and after interpolate with k-epsilon equations solutions &
introduce the velocity by components (from 10 to -10 degrees; taking 20 & -20 as extreme
values); taking 50 as Speed Module
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Setting XFLOW for 3D analysis
We start setting velocity as 50 m/s and the wind tunnel dimensions (2,2,2)
In orientation field, we have to set the angle of attack we want to analyze.
We set the simulation time & the scale which XFLOW will used as a mesh; we have to set the
frames frequency as well.
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Change the surface info part & the field too to obtain (Vorticity, Static Pressure, Cp
Distribution, and Velocity by Components) for each degree we have analyzed; to obtain the
graphs we will see later.
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0 Degree Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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2 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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5 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Velocity in X-Component
Velocity in Y-Component
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6 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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7 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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8 degrees Angle of Attack
Cp distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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10 Degrees Angle of Attack
Cp Distribution
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Static Pressure
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Vorticity
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Velocity in X-Component
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Velocity in Y-Component
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20 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-2 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-5 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-6 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-7 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-8 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-10 Degrees Angle of Attack
Cp Distribution
Static Pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
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-20 Degrees Angle of Attack
Cp Distribution
Static pressure
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Vorticity
Velocity in X-Component
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Velocity in Y-Component
At the same time we obtain those previous graphs with contours and surfaces distributions;
we obtain de Lift, Drag & Moment in Z-Component Coefficients for each angle of attack
previously analyzed.
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We use those values to create some plotted graphs to observe when the wing could be
consider stable.
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FINAL CONCLUSSION GRAPHS
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As we can see in the 2D graphs get with XFLR5 and compared with those ones we have obtain
or the 3D analysis with XFLOW, we can conclude that the stable zone for the wing that we
have study in our project is between the -5 to 0 degrees angle of attack region. Out of these
region, the wing can behaves in very rare ways; giving us a lot of lift or a lot of drag for 3
degrees variation.
Our wing does not behaves as a symmetric airfoil profile could behaves; even we have taken
the N-10 ideal airfoil design; but the interpolation with our approach measurements, change
completely the results of the analysis.
We can conclude that for the aerodynamic analysis of a wing we cannot take measurements