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Supersonic second order analysis and optimization program user's manualApproximate nonlinear inviscid theoretical techniques for predicting aerodynamic characteristics and surface pressures for relatively slender vehicles at supersonic and moderate hypersonic speeds were developed. Emphasis was placed on approaches that would be responsive to conceptual configuration design level of effort. Second order small disturbance theory was utilized to meet this objective. Numerical codes were developed for analysis and design of relatively general three dimensional geometries. Results from the computations indicate good agreement with experimental results for a variety of wing, body, and wing-body shapes. Case computational time of one minute on a CDC 176 are typical for practical aircraft arrangement.
Document ID
19870001409
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Clever, W. C. (Rockwell International Corp. Los Angeles, CA, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-172342
NAS 1.26:172342
Accession Number
87N10842
Funding Number(s)
CONTRACT_GRANT: NAS1-15820
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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