The transonic phase of the 0.0088105-scale MSC orbiter booster separation test was conducted in the LTV 4-foot high speed wind tunnel, at Mach numbers of 0.6,0.9, 1.1, and 1.38. The purpose of this test was to define the effects of the orbiter/ booster proximity interference on the aerodynamic characteristics of the launch configuration during separation or abort maneuvers. Each model had both straight and delta wings available for variation of launch vehicle configuration concepts.
Space shuttle: Effect of orbiter/booster proximity interferences on the aerodynamic characteristics of the launch configuration during separation or abort maneuvers, M equals 0.6 - 1.38
1971-07-01
Report
No indication
English