PRESSURE DISTRIBUTIONS ON A HEMISPHERE CYLINDER AT SUPERSONIC AND HYPERSONIC MACH NUMBERS
- 1 August 1961
- report
- Published by Defense Technical Information Center (DTIC)
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.Keywords
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