Development of a Computer Program to Calculate Aerodynamic Characteristics of Bodies and Wing-Body Combinations.
Interim rept. 15 Dec 76-15 Dec 77,
NORTH CAROLINA STATE UNIV RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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A new method has been developed for calculating an approximate surface pressure distribution over axisymmetric bodies, with pointed or blunted noses, at angle of attack in supersonic flow. A modified form of the second-order shock-expansion method is developed and matched to modifed Newtonian theory near the nose. Surface pressure distributions compared well with experimental data on blunted cones with and without flares at Mach numbers from 1.5 to 4.63 and angles of attack to 12 deg. Author
- Fluid Mechanics