This report presents the results of a wind-tunnel investigation of a hemisphere-cylinder configuration with an aerodynamic spike produced by a small nozzle exhausting air from the center of the hemispherical nose at supersonic speeds. The tests were conducted in the 18-Inch Supersonic Wind Tunnel of the Gas Dynamics Facility at test-section Mach numbers of 1.87 and 2.16. The effects of angle of attack and supply pressure upon the longitudinal aerodynamic and heat-transfer characteristics are indicated.
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