Pressure Distributions on a Hemisphere Cylinder at Supersonic and Hypersonic Mach Numbers
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Report Number: AEDC TN 61-96
Author(s): Baer, A. L.
Corporate Author(s): VKF, ARO, Inc.
Date of Publication: 1961-08
Pages: 34
Contract: AF 40(600)-800
DoD Project: None Given
Identifier: AD0261501
Abstract:
Pressure distribution tests at supersonic and hypersonic speeds were conducted in the von Karman Gas Dynamics Facility (VKF), Arnold Center, Air Force Systems Command on AGARD Model E, a hemisphere cylinder configuration. Various experimental data concerning the aerodynamic characteristics of blunt nosed bodies are available; however, relatively few sources present findings over a wide arch number range. The present investigations, stimulated by the need for applicable experimental data to compare with the predictions of various theories, were conducted a Mach numbers 2 through 8 over a Reynolds number range from 0.17 x 10 to the 6th power to 0.51 x 10 to the 6th power per inch. A comparison is made of experimental results with available theoretical predictions of pressure distributions, pressure drag, shock wave shapes, and bow shock wave detachment distances.
Provenance: IIT
Author(s): Baer, A. L.
Corporate Author(s): VKF, ARO, Inc.
Date of Publication: 1961-08
Pages: 34
Contract: AF 40(600)-800
DoD Project: None Given
Identifier: AD0261501
Abstract:
Pressure distribution tests at supersonic and hypersonic speeds were conducted in the von Karman Gas Dynamics Facility (VKF), Arnold Center, Air Force Systems Command on AGARD Model E, a hemisphere cylinder configuration. Various experimental data concerning the aerodynamic characteristics of blunt nosed bodies are available; however, relatively few sources present findings over a wide arch number range. The present investigations, stimulated by the need for applicable experimental data to compare with the predictions of various theories, were conducted a Mach numbers 2 through 8 over a Reynolds number range from 0.17 x 10 to the 6th power to 0.51 x 10 to the 6th power per inch. A comparison is made of experimental results with available theoretical predictions of pressure distributions, pressure drag, shock wave shapes, and bow shock wave detachment distances.
Provenance: IIT