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A simplified shock-fitting solution to a supersonic internal corner flowfieldA simplified shock-fitting method is developed and applied to a supersonic internal corner flowfield. An analytical approach is discussed, and results for a case with a free-stream Mach number of 2.47 and wedge angles of 12.2 deg are shown.
Document ID
19800057445
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Martin, J. A. (NASA Langley Research Center Space Systems Div., Hampton, Va., United States)
Date Acquired
August 10, 2013
Publication Date
July 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-1425
Report Number: AIAA PAPER 80-1425
Meeting Information
Meeting: Fluid and Plasma Dynamics Conference
Location: Snowmass, CO
Start Date: July 14, 1980
End Date: July 16, 1980
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
80A41615
Distribution Limits
Public
Copyright
Other

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