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Nonlinear potential analysis techniques for supersonic-hypersonic configuration designApproximate nonlinear inviscid theoretical techniques for predicting aerodynamic characteristics and surface pressures for relatively slender vehicles at moderate hypersonic speeds were developed. Emphasis was placed on approaches that would be responsive to preliminary configuration design level of effort. Second order small disturbance and full potential theory was utilized to meet this objective. Numerical pilot codes were developed for relatively general three dimensional geometries to evaluate the capability of the approximate equations of motion considered. Results from the computations indicate good agreement with higher order solutions and experimental results for a variety of wing, body and wing-body shapes for values of the hypersonic similarity parameter M delta approaching one. Case computational times of a minute were achieved for practical aircraft arrangements.
Document ID
19850021605
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Clever, W. C. (Rockwell International Corp. Los Angeles, CA, United States)
Shankar, V. (Rockwell International Corp. Los Angeles, CA, United States)
Date Acquired
September 5, 2013
Publication Date
March 28, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166078
NA-82-1170
NAS 1.26:166078
Accession Number
85N29917
Funding Number(s)
CONTRACT_GRANT: NAS1-15820
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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