Heat-Transfer and Flow-Field Tests of the North American Rockwell/ General Dynamics Convair Space Shuttle Configurations
Final rept. Jun-Sep 1971
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American RockwellGeneral Dynamics Convair were conducted at Mach number 8. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry including leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry