After the STS 51-L accident, an extensive review of the Space Shuttle Orbiter's ascent aerodynamic loads uncovered several questionable areas that required further analysis. The insight gained by comparing the Shuttle ascent CFD numerical simulations, obtained by the NASA Ames Space Shuttle Flow Simulation Group, to the current IVBC-3 aerodynamic loads database was instrumental in resolving uncertainties on the Orbiter payload bay doors and fuselage. Initial confidence in the numerical simulations was gained by comparing them with the limited flight data that had been obtained during the Orbiter Flight Test (OFT) program. Current CFD results exist for Mach numbers 0.6, 0.9, 1.05, 1.55, 2.0, and 2.5. Since the pre STS-1 wind tunnel test program (IA-105) often yields considerable differences when compared to STS-5 flight data, the M(sub infinity) = 1.05 transonic case is the most investigated. The IA308 mated-vehicle hot gas plume wind tunnel test, recently completed at AEDC 16T (transonic) and Lewis (hypersonic), is also used to compare with the computation where applicable.
Numerical Aerodynamic Simulation of the Space Shuttle Ascent Environment
1989
15 pages
Report
Keine Angabe
Englisch
Astronautics , Manned Spacecraft , Aerodynamics , Ascent , Computational fluid dynamics , Computerized simulation , Space shuttle orbiters , Aerodynamic loads , Aerospace environments , Mathematical models , Data bases , High temperature gases , Hypersonics , Plumes , Space transportation system , Subsonic speed , Wind tunnel tests
Shuttle system ascent aerodynamic and plume heating
NTRS | 1985
|Tema Archiv | 1989
|SAE Technical Papers | 1989
|