Force and Moment Tests to Determine the Interaction Effects of the Reaction Control System Jet Plumes on the Space Shuttle Orbiter Aerodynamics at Mach Number 6 (Test OA352). Final Report,January 20-February 6, 1987,

摘要

The purpose of this test was to expand the existing Space Shuttle aerodynamics and Reaction Control System (RCS) data base to support the Glide Return to Launch Site (GRTLS) abort trajectory and the new Digital Autopilot. An existing model of the orbiter was used to investigate the aerodynamic effects of several combinations of RCS thrusters and thruster momentum ratios at Mach number 6. Two separate model installations were used to achieve an angle-of-attack range of -11 to 46 deg. The test was conducted at a unit Reynolds number of 0.8 x 10 to the 6th per foot.