Numerical Simulations of Hypersonic Real-Gas Flows Over Space Vehicles 912045
Hypersonic flows over simple 3-D bodies and a space vehicle are simulated using a real-gas Navier- Stokes code under an equilibrium air assumption. This code is based on 3-D upwind flux splitting scheme with generalized Roe's Riemann solver. The real-gas effect is incorporated using the VEG (Variable Equivalent Gamma) method [1]*. The equivalent gamma and other thermodynamic properties are calculated using empirical curve fits [2].
Numerical simulations are conducted for flow fields around a spherical blunt body, a spherical-nose cylinder, and a cone-cylinder as simple configurations, and HOPE (H-orbiting plane: Japanese spaceplane) as a practical plane configuration. Flow conditons are Mach numbers of 7.72, 15.0 for the blunt bodies, 6.86 for the cone-cylinder, and 15.0 for the HOPE. Computed pressure and density distributions are presented. Results for simple configuration cases are compared with experimental data for the code validation.
Citation: Nakao, M. and Fujii, K., "Numerical Simulations of Hypersonic Real-Gas Flows Over Space Vehicles," SAE Technical Paper 912045, 1991, https://doi.org/10.4271/912045. Download Citation
Author(s):
Masahiro Nakao, Kozo Fujii
Pages: 8
Event:
International Pacific Air & Space Technolgy Conference
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
International Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings-P-246
Related Topics:
Spacecraft
Engine cylinders
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