Abort Separation, Longitudinal Force, and Moment Characteristics of McDonnell Douglas Booster and Orbiter Space Shuttle Vehicles at Mach Numbers 2.0 to 6.0.
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
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Results are presented for abort staging wind tunnel tests which were conducted to determine the aerodynamic characteristics of the McDonnell Douglas booster and orbiter configurations in close proximity. Data were obtained on both scale models over an angle-of-attack range from -10 to 10 deg for zero slideslip angle. Orbiter incidence angle relative to the booster was varied from -10 to 10 deg which provided an orbiter angle-of-attack range from -20 to 20 deg. The models were tested at Mach numbers from 2.0 to 6.0 at several separation distances and power conditions. An annular cold-flow nozzle in each model was used to simulate booster and orbiter plumes at various altitudes along a proposed ascent trajectory. Plume simulation for 100, 50, and 0 percent of full power for the booster and 100, 50, 25, and 1 percent of full power for the orbiter was investigated, with 50-percent booster and 100-percent orbiter power as the nominal conditions. Pitch control effectiveness data were obtained for both booster and orbiter with power on and off. In addition, data were obtained with and without booster power simulation on a proposed launch configuration where the orbiter was physically attached to the booster, and a single balance in the booster model was utilized. A complete set of plotted data for each vehicle at each test condition is included. Author
- Unmanned Spacecraft