SPACE SHUTTLE ABORT SEPARATION PRESSURE INVESTIGATION VOLUMEⅠ PART B BOOSTER DATA AT MACH 5

摘要

This report presents pressure data obtained from a joint Langley Research Center (LaRC)/Marshall Space Flight Center (MSFC) Space Shuttle abort stage separation wind tunnel test. The .00556 scale models of the McDonnell-Douglas orbiter and booster configurations were tested in proximity in Tunnel A of the Von Karman Facility (VKF), Arnold Engineering Development Center (AEDC) during the time period of July 22 to July 27, 1971. Data were obtained for nominal Mach numbers of 5.0, 3.0, and 2.0 and nominal Reynolds numbers of 1.09, 1.60, and 1.74 million per foot, respectively. Pressure data were obtained for the booster upper surface and orbiter lower surface at angles of attack of -10°, -5, 0, 5, and 10° for zero degrees sideslip. For the complete pressure tap layout refer to figures 1 and 2 and tables II and III. The models were tested at inci¬dence angles of 0 and 5° for several separation distances and power conditions. Plug nozzles utilizing air were used to simulate booster and orbiter plumes at various altitudes along a nominal ascent trajectory. Powered conditions were 100, 50, and 0 percent of full power for the orbiter and 100, 50 and 0 percent of full power for the booster. Data were also obtained with the booster canard off in close proximity.