These tests were conducted to obtain longitudinal stability and control data for Mach numbers from 0.35 to 1.2. Data were obtained for an alpha range of -2 deg to +22 deg at beta = 0 deg. The effect of speedbrake deflection and body flap deflection was obtained through the Mach range. Boundary layer transition strips were used on the model. (Author)
Wind Tunnel Tests of an 0.015-Scale Configuration 140A/B Space Shuttle Orbiter Model (67-0) in the NASA/Lrc 8-Foot Tpt to Obtain Transonic Aerodynamic Force Data (OA106)
1974
197 pages
Report
No indication
English