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Internal hypersonic flowAn approach for studying hypersonic internal flow with the aid of a thin-shock-layer approximation is discussed, giving attention to a comparison of thin-shock-layer results with the data obtained on the basis of the imposition theory or a finite-difference integration of the Euler equations. Relations in the case of strong interaction are considered together with questions of pressure distribution and aspects of the boundary-layer solution.
Document ID
19740043366
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lin, T. C.
(New York, Polytechnic Institute, Farmingdale, N.Y.; NASA, Marshall Space Flight Center Huntsville, Ala., United States)
Rubin, S. G.
(New York, Polytechnic Institute, Farmingdale, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
March 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 73-APM-DD
AD-A000739
AFOSR-74-1643TR
Accession Number
74A26116
Funding Number(s)
OTHER: AF-AFOSR-70-1843
PROJECT: AF PROJECT 9781-01
Distribution Limits
Public
Copyright
Other

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