AN ENGINEERING METHOD FOR RAPID CALCULATION OF SUPERSONIC-HYPERSONIC PRESSURE DISTRIBUTIONS ON LIFTING AND NON-LIFTING POINTED BODIES OF REVOLUTION AND SEVERAL SPECIAL CASES OF BLUNT-NOSED BODIES OF REVOLUTION
JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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The method, which utilized hybrid tandem solutions involving Generalized Newtonian and Shock-Expansion theories, provides accurate results for a variety of nose shapes and fineness ratios over a range of supersonic hypersonic Mach numbers. The numerical simplicity of the method, which makes it readily applicable for quick hand-calculational procedures, was the prime factor in its selection and publication. The investigation for lifting bodies indicates the present method is applicable for bodies of revolution at angles of attack up to about ten degrees. The report presents numerical examples showing stepwise calculational procedures for obtaining pressure coefficient and local Mach number distributions along the meridians of a body of revolution at angle of attack.
- Fluid Mechanics