Effects of Reaction Control System Jet Flow Field Interactions on the Aerodynamic Characteristics of a 0.010-Scale Space Shuttle Orbiter Model in the Langley Research Center 31 Inch Cfht (OA85)
Effects of Reaction Control System Jet Flow Field Interactions on the Aerodynamic Characteristics of a 0.010-Scale Space Shuttle Orbiter Model in the Langley Research Center 31 Inch Cfht (OA85)
- New search for: J. J. Daileda
- New search for: J. Marroquin
- New search for: J. J. Daileda
- New search for: J. Marroquin
An experimental investigation was conducted to obtain detailed effects on supersonic vehicle hypersonic aerodynamic and stability and control characteristics of reaction control system jet flow field interactions with the local vehicle flow field. A 0.010-scale model was used. Six-component force data and wing, elevon, and body flap surface pressure data were obtained through an angle-of-attack range of -10 to +35 degrees with 0 deg angle of sideslip. The test was conducted with yaw, pitch and roll jet simulation at a free-stream Mach number of 10.3 and reaction control system plume simulation of flight dynamic pressures of 5, 10 and 20 PSF. (Author)
Document information
Effects of Reaction Control System Jet Flow Field Interactions on the Aerodynamic Characteristics of a 0.010-Scale Space Shuttle Orbiter Model in the Langley Research Center 31 Inch Cfht (OA85)
1974
202 pages
Report
No indication
English