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A method for predicting shock shapes and pressure distributions on two dimensional airfoils at large angles of attackA method is presented for determining shock envelopes and pressure distributions for two-dimensional airfoils at angles of attack sufficiently large to cause shock detachment and subsonic flow over the windward surface of the airfoil. Correlation functions obtained from exact solutions are used to relate the shock standoff distance at the stagnation and sonic points of the body through a suitable choice for the shock shape. The necessary correlation functions were obtained from perfect gas solutions but may be extended to any gas flow for which the normal shock-density ratio can be specified.
Document ID
19730009274
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Kaattari, G. E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-7197
A-4564
Accession Number
73N18001
Funding Number(s)
PROJECT: RTOP 117-07-02-01-00-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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