Experimental aerodynamic investigations were conducted on a stingmounted 0.0405-scale representation of the 140A/B space shuttle orbiter in a 7.75 by 11-Foot low speed wind tunnel from April 24 to April 26, 1974. Differential inboard/outboard elevon panel deflections with the 6-inch gap were investigated to determine outboard panel aileron effectiveness. The elevons were deflected from +20 degrees to -40 degrees in various combinations. Aerodynamic force and moment data for the orbiter were measured in the body axis system by an internally mounted, six-component strain gage balance. The model was sting mounted with the center of rotation located at F.S. 60.172. The angle of attack range was from -10 degrees to +24 degrees.
Effect of ELEVON gap configurations on the longitudinal stability and control effectiveness of the 43-0 space shuttle orbiter (OA118)
1974-08-01
Report
Keine Angabe
Englisch
Thermal analysis of Shuttle Orbiter wing/elevon seals
AIAA | 1984
|Space shuttle elevon seal panel mechanism
NTRS | 1985
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