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Lee side flow for slender delta wings of finite thicknessAn experimental and theoretical investigation carried out to determine the lee side flow field over delta wings at supersonic speeds is presented. A theoretical method to described the flow field is described, where boundary conditions as a result of the experimental study are needed. The computed flow field with shock induced separation is satisfactory.
Document ID
19800014764
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Szodruch, J. G. (NASA Headquarters Washington, DC United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-75753
ILR-23
Accession Number
80N23253
Funding Number(s)
CONTRACT_GRANT: NASW-3198
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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