Supersonic And Hypersonic Rocket Analysis 425ls

HyperCFD 2.5 Supersonic and Hypersonic Rocket Analysis Purchase | MAIN PAGE | PRODUCTS | CONSULTING | MISSION | RESUME | Copyright © 1999-2014 John Cipolla/AeroRocket

HyperCFD™ 2.5.1 Supersonic and Hypersonic Rocket Analysis using 3-D Gasdynamics Determine drag coefficient (Cd), center of pressure (X), CN-alpha and Cm-alpha of supersonic and hypersonic rockets and re-entry vehicles. In addition, on a separate screen HyperCFD displays and plots CN-Body, CN-Fins, CN-Total and Cm-Total as a function of angle of attack (AOA) u/down controls. HyperCFD uses empirical corrections to the modified Newtonian surface inclination method that allows excellent results from Mach 1.05 to Mach 20. Includes a wide variety of nose cone shapes and fin cross-sections. Nose cone shapes include, conical, elliptical, parabolic, power series Sears-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 location for level 3 flights. New in this description is a methodology to determine heat loads into the airframe of supersonic and hypersonic rockets using temperature distribution (T/Tinf) results from HyperCFD and AeroCFD. The following links clearly illustrate how HyperCFD has been used to analyze re-entry vehicles. Revisiting China’s Early Warhead Designs Iranian Warhead Evolution New Features 1) 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 X 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

HyperCFD main screen displaying re-entry vehicle

HyperCFD re-entry vehicle pressure distribution

Case #2: Conical Nose Cone

Case #3: Missile With Fins

Hypersonic missile In free flight

HyperCFD main screen displaying hypervelocity missile

HyperCFD fin geometry screen for hypervelocity missile

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

HyperCFD Motor On/Off screen

HyperCFD Biconic Re-Entry Vehicle

HyperCFD analysis of a Biconic re-entry vehicle operating at Mach 5 to determine Cd (drag coefficient), X (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.

HyperCFD analysis of the Mars Phoenix entry capsule operating at Mach 18.5 to determine Cd, X 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 supersonic 2 vehicle. First, the heating rate per area, q (J/sec-m ) is defined as, q = k (Tr - Tw) where k is the convective heat transfer 2 coefficient (J/m -sec-K), Tr is the recovery or stagnation temperature, T w is the wall temperature and r is the recovery factor which is equal to 1 for this example. Both temperatures are defined in degrees Kelvin (K). Wall temperature is computed using HyperCFD or AeroCFD and is derived from the ratio of T/Tinf where Tinf is the local atmospheric temperature and T is the wall temperature (Tw). The example below (second image) determines wall temperature, recovery temperature and maximum heat load into the airframe near the nose tip of a supersonic or hypersonic rocket. For this example Prandtl 2 number (Pr) and recovery factor (r) both equal 1 and k = 235 J/m -sec-K.

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

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

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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