Aerodynamic investigations were conducted in a transonic pressure tunnel on an 0.015 scale model of the space shuttle orbiter. Major test objectives were to determine: (1) transonic differential elevon/aileron lateral control optimization; (2) transonic elevon hinge moments; (3) transonic effects of the baseline 6 inch elevon/elevon and elevon/fuselage gaps; and (4) transonic effects of the short OMS pods. Six-component aerodynamic force and moment, and elevon hinge moment data, were recorded over an angle-of-attack range form -2 to +22 degrees. (Author)
Results of Differential Elevon/Aileron Deflection for Lateral Control Optimization and Elevon Hinge Moment Investigations on an 0.015-Scale Model (49-0) of the Space Shuttle Orbiter in the NASA/Langley Research Center 8 Foot Tpt (OA116)
1974
278 pages
Report
Keine Angabe
Englisch