Results of investigations on an 0.015-scale model (49-0) of the Rockwell International Space Shuttle orbiter in the NASA-Ames Research Center 3.5-foot hypersonic wind tunnel (0A98)

The results of a wind tunnel test are presented; the model used for this test was 0.015-scale 140 A/B hybrid configuration of the space shuttle orbiter. The primary test objectives were to obtain incremental data on the effects of a sting mount on base pressures and force and moment data. The increments obtained included the addition of MPS nozzles as well as the deletion of the simulated sting mount. Six-component aerodynamic force and moment data were recorded over an angle of attack range from 12 to 42 degrees at 0 and 5 degrees angles of sideslip. The testing was accomplished at Mach 5.3 and Mach 10.3. The effects of various elevon, body flap, and speed brake settings were investigated, and static pressures were measured at the fuselage base for use in force-data reduction.