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Higher-Order Panel Method for Aerodynamic Flow AnalysisPANAIR uses high-order panel method to predict inviscid subsonic or supersonic flows about arbitrary configuration. Panel method solves linear partial differential equation numerically by approximating configuration surface with panels on which unknown "singularity strengths" are defined. PANAIR includes advanced software technology as well as advanced aerodynamic technology.
Document ID
19820000064
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Erickson, L. (Boeing Computer Services)
Carmichael, R. L. (Boeing Computer Services)
Levin, A. D. (Boeing Computer Services)
Magnus, A. (Boeing Computer Services)
Epton, M. (Boeing Computer Services)
Baruah, P. (Boeing Computer Services)
Massena, B. (Boeing Computer Services)
Bussoletti, J. (Boeing Computer Services)
Sidwell, K. (Boeing Computer Services)
Johnson, F. (Boeing Computer Services)
Zeppa, J. (Boeing Computer Services)
Bates, G. (Boeing Computer Services)
Clemens, D. (Boeing Computer Services)
Derbyshire, T. (Boeing Computer Services)
Purdon, D. (Boeing Computer Services)
Chiang, D. (Boeing Computer Services)
Rubbert, P. (Boeing Computer Services)
Nelson, F. (Naval Coastal Systems Center)
Wai, J. (Wright Patterson AFB)
Tsurusaki, K. (Wright Patterson AFB)
Smith, N. (USAF Academy)
Snyder, J. R. (Langley Research Center)
Sotomayer, W. (Langley Research Center)
Dejongh, J.
Thomas, J. L.
Date Acquired
August 10, 2013
Publication Date
December 1, 1982
Publication Information
Publication: NASA Tech Briefs
Volume: 6
Issue: 4
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
ARC-11398
Accession Number
82B10064
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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