EFFECTS OF THE SIX ENGINE AIR BREATHING PROPULSION SYSTEM ON SPACE SHUTTLE ORBITER SUBSONIC STABILITY AND CONTROL CHARACTERISTICS(OA71C)

摘要

Experimental aerodynamic investigations were conducted on an 0.0405 scale representation of the -89B Space Shuttle Orbiter in the Rockwell International 7.75 x 11.00 Foot Low Speed Wind Tunnel during the time period September 4 - 14, 1973. The NASA designation for this test was 0A71C.nThe primary test objective was to optimize the air breathing propulsion system nacelle cowl-inlet design and to determine the aerodynamic effects of this design on the orbiter stability and control characteristics. Nacelle cowl-inlet optimization was determined from total pressure static pressure measurements obtained from pressure rakes located in the left hand nacelle pod at the engine face station (see figure 3).