Experimental aerodynamic investigations were conducted on a sting-mounted 0.0405 scale representation of the 140A/B space shuttle orbiter in a 7.75 ft by 11 ft low speed wind tunnel during the time period from November 14, 1973, to December 6, 1973, with the primary test objectives being to establish basic longitudinal stability characteristics in and out of ground effect, as well as lateral-directional stability characteristics in free air. Two dual podded nacelle configurations were also tested, one with three dual podded nacelles on the lower wing surface, and the other with a single dual nacelle on the lower centerline with dual nacelle pylons mounted above each wing. Stability and control characteristics were investigated at nominal elevon, rudder, aileron, and body flap deflections. Pressure bugs were used to determine pressures on the vertical tail at spanwise stations, and aerodynamic force and moment data were measured in the stability axis system by an internally mounted, six component strain gage balance. (Author)
Investigation of Space Shuttle Orbiter Subsonic Stability and Control Characteristics in the Naal Low Speed Wind Tunnel (0A62B), Volume 1
1974
1010 pages
Report
No indication
English
Manned Spacecraft , Aerodynamic characteristics , Control stability , Low speed wind tunnels , Space shuttle orbiters , Subsonic speed , Aerial rudders , Aerodynamic forces , Ailerons , Deflection , Elevons , Ground effect , Longitudinal stability , Nacelles , Pods (External stores) , Pressure sensors , Scale models , Stability derivatives , Strain gages