BOUNDARY-LAYER, PRESSURE, AND TEMPERATURE DISTRIBUTION STUDIES ON SEVERAL ISENTROPIC COMPRESSION SURFACES AT MACH NUMBERS FROM 4 TO 8
Technical documentary rept.
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Boundary-layer, pressure, and temperature measurements were obtained on the generating cylinder and isentropic compression surface of several axisymmetric hypersonic inlet configurations at supersonic and hypersonic Mach numbers. Boundary-layer surveys were performed at selected stations on uncooled Mach 5, 6, and 10 inlets and a cooled Mach 8 inlet. Model surface temperatures and pressures were obtained at several Mach numbers on all configurations. Steady-state heat transfer data were obtained on the Mach 8 inlet at several model wall temperatures. Selected results from the tests are presented.