supersonic and hypersonic rocket analysis

8/10/2019 Supersonic and Hypersonic Rocket Analysis

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HyperCFD 2.5Supersonic and Hypersonic Rocket Analysis

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HyperCFD2.5.1

Supersonic and Hypersonic Rocket Analysis using 3-D GasdynamicsDetermine drag coefficient (Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic and hypersonic rocketsand re-entry vehicles. In addition, on a separate screen HyperCFD displays and plots CN-Body, CN-Fins, CN-Total andCm-Total as a function of angle of attack (AOA) using up/down controls. HyperCFD uses empirical corrections to themodified Newtonian surface inclination method that allows excellent results from Mach 1.05 to Mach 20. Includes a widevariety of nose cone shapes and fin cross-sections. Nose cone shapes include, conical, elliptical, parabolic, power seriesSears-Haack, tangent ogive and spherical segment. Fin cross-sections include single wedge, symmetrical double wedge,arbitrary double wedge, biconvex section, streamline section, round-nose section, and elliptical section fin shapes.HyperCFD is useful to determine supersonic rocket drag and Cp location for level 3 flights. New in this description is amethodology to determineheat loadsinto the airframe of supersonic and hypersonic rockets using temperaturedistribution (T/Tinf) results from HyperCFD andAeroCFD.

The following links clearly illustrate how HyperCFD has been used to analyze re-entry vehicles.Revisiting Chinas Early Warhead DesignsIranian Warhead Evolution

New Features1) Temperature on the surface of the rocket relative to free-stream conditions.2) Pressure and temperature can be output to a PLT file and read as a text file.3) Cd estimation as a function of AOA based on Newtonian surface inclination theory.4) Cd estimation and XCp estimation as a function of small angle of attack (1 to 2 degrees).5) Cd estimation for decreasing cross-sectional components.

HyperCFD Results

Case #1: Re-Entry Vehicle
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HyperCFD main screen displaying re-entry vehicle


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HyperCFD re-entry vehicle pressure distribution

Case #2: Conical Nose Cone


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Case #3: Missile With Fins

Hypersonic missile In free flight

HyperCFD main screen displaying hypervelocity missile


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HyperCFD fin geometry screen for hypervelocity missile


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HyperCFD aerodynamic coefficients as a function of AOA on body, fins and fin-body.


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HyperCFD Motor On/Off screen


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HyperCFD Biconic Re-Entry Vehicle


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HyperCFDanalysis of a Biconic re-entry vehicle operating at Mach 5 to determine Cd (drag coefficient), Xcp (center of pressure) and CNa (lift slope)

Mars Phoenix Entry Capsule Aerodynamics

Orientation of the Mars Phoenix entry capsule. Image not the result of HyperCFD.


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HyperCFDanalysis of the Mars Phoenix entry capsule operating at Mach 18.5 to determine Cd, Xcp and CNa.

Wall Temperature, Recovery Temperature and Airframe Heat Rate

This is a simplified discussion of the interaction between vehicle dynamics and heat loads on the airframe of a supersonicvehicle. First, the heating rate per area, q (J/sec-m

2) is defined as, q = k (Tr- Tw) where k is the convective heat transfer

coefficient (J/m2-sec-K), Tris the recovery or stagnation temperature, Twis the wall temperature and r is the recovery facto

which is equal to 1 for this example. Both temperatures are defined in degrees Kelvin (K). Wall temperature is computedusing HyperCFDor AeroCFDand is derived from the ratio of T/Tinf where Tinf is the local atmospheric temperature and Tis the wall temperature (Tw). The example below (second image) determines wall temperature, recovery temperature andmaximum heat load into the airframe near the nose tip of a supersonic or hypersonic rocket. For this example Prandtlnumber (Pr) and recovery factor (r) both equal 1 and k = 235 J/m

2-sec-K.


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HyperCFDanalysis of a hypersonic missile to determine airframe temperature distribution (T/Tinf).


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Example to determine wall temperature, recovery temperature and airframe heat rate of a hypersonic rocket


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SYSTEM REQUIREMENTS(1) Screen resolution: 800 X 600(2) System: Windows 98, XP, Vista, Windows 7 (32 bit and 64 bit), NT or Mac with emulation(3) Processor Speed: Pentium 3 or 4(4) Memory: 64 MB RAM(5) English (United States) Language(6) 256 colors

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supersonic and hypersonic rocket analysis

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