RESULTS OF LOW SPEED WIND TUNNEL TESTS ON A .OU05 SCALE MODEL ROCKWELL SPACE SHUTTLE ORBITER TESTED BOTH IN FREE AIR AND IN THE PRESENCE OF A GROUND PLANE (φA16)

摘要

The ground plane portion of the aerodynamic test investigated the same aforementioned nacelle effects at ground plane locations of full scale W. P.=239.9, 209.3, 158.9, 108.5, and 7.78 in. The model was supported in the same manner with the nominal angle of attack range being 40≤a≦24°) except where ground plane limited. No sideslip data were recorded. ELevon deflections from 15° to -40° and an aileron deflection of 10° (elevon = 0°) were tested.nAt the conclusion of the aerodymamic test period the propulsion effects of various nacelle locations and frefstream orientations in the presence of the ground were investigated. This investigation consisted of positioning the engine nacelles at various chordwise positions and angles of sideslip and then recording the total pressure recovery-mass flow relationship at the compressor face station. Nacelle internal flow characteristics were calculated from two flow-metering rakes that could be positioned in any nacelle. Engine weight flows of .15, .25, .35, and ,45 lbm/see/eng. were simulated.