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HEMISPHERE-CYLINDER PRESSURE DISTRIBUTIONS AT SUPERSONIC AND HYPERSONIC MACH NUMBERS
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pressure distributions on a hemisphere-cylinder at a Mach number of 10 and at angles of attack up to 25 deg are presented. These experimental distributions are compared with hypersonic blunt-body analytical and numerical solutions. Experimental stagnation point velocity gradients, sonic point locations, and pressure drag coefficients for hemispheres at Mach numbers from 1.8 to 21 have been compiled, and empirical relations are developed for these parameters as functions of Mach number.
Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. DOI: 10.21236/AD0804001
Approved for public release; distribution is unlimited.
Contract Number 2: