HYPERSONIC FLOW AROUND BLUNT BODIES OF REVOLUTION WHOSE SHOCK WAVES ARE GENERATED BY CONIC SECTIONS. Paper 8 of GENERAL RESEARCH IN FLIGHT SCIENCES, JANUARY 1959-JANUARY 1960. VOLUME I. FLUID MECHANICS. PART 1
Technical Report
·
OSTI ID:4178501
The inviscid hypersonic blunt body problem is considered. The procedure given by Lighthill for the special case of a spherical shock wave is extended to the family of conic shock shapes. Two approximations are required that limit the solution to the axis of symmetry. After the solution is obtained. certain flow parameters are calculated and (for three particular shock shapes) are compared with results from the numerical methods of Van Dyke and Mangler. (auth)
- Research Organization:
- Lockheed Aircraft Corp. Missiles and Space Div., Sunnyvale, Calif.
- NSA Number:
- NSA-14-019089
- OSTI ID:
- 4178501
- Report Number(s):
- LMSD-288139(Vol. I, Pt. 1)(Pap
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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