Pressure And Heat Transfer Measurements For Mach 8 Flows Over A Blunt Pryamidal Configuration With Aerodynamic Controls
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Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 8 heat transfer data for flows ahead of ramps
"Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.