A hypersonic shock tunnel test on a 0.010 scale SSV orbital configuration was performed to determine the effects of RCS jet/flow field interactions on SSV aerodynamic stability and control characteristics at various hypersonic Mach and Reynolds numbers. Flow field interaction data were obtained using pitch and roll jets. In addition, direct impingement data were obtained at a Mach number of zero with the test section pumped down to below 10 microns of mercury pressure. (Author)
Results of Wind Tunnel RCS Interaction Tests on a 0.010-Scale Space Shuttle Orbiter Model (51-0) in the Calspan Corporation 48-Inch Hypersonic Shock Tunnel (Test 0A93)
1976
115 pages
Report
Keine Angabe
Englisch