PRESSURE DISTRIBUTIONS ON A HEMISPHERE CYLINDER AT SUPERSONIC AND HYPERSONIC MACH NUMBERS
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
Pagination or Media Count:
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.
- Theoretical Mathematics