Heat-Transfer Tests of Two Space Shuttle Orbiter Configurations at Mach Number 8
Final rept. 25 Aug-28 Sep 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Heat transfer tests were conducted on two Space Shuttle configurations at Mach number 8 to investigate the effects of nose geometry on windward and leeward heating and boundary layer transition. Free-stream Reynolds number based on model length was varied from 1.5 to 7.5 million at angles of attack from 20 to 50 deg. Windward centerline heating rates were in general agreement with calculated values except for laminar rates dowstream of the wing body junction. Differences in the location of the beginning of transition and the length of the transition zone were observed for the two configurations, but it was not clear whether variation in nose shape per se or the abrupt cross- sectional change from the nose to the aft fuselage and wing was the controlling factor.
- Spacecraft Trajectories and Reentry
- Manned Spacecraft