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Modeling techniques for transonic airfoilsIn the present comparative study of computer codes for the modeling of two-dimensional, single element airfoil sections for various section geometry classes, two of the codes use vortex singularities methods to obtain the potential flow solution while the remainder solve the full inviscid potential flow equations by means of finite differencing techniques that allow results to be obtained for transonic flow about an airfoil which includes weak shocks. Computational results are presented for a symmetrical airfoil section, a conventional section, and a supercritical one. Icing condition applications of the models are noted. The model codes' range of applicability and agreement with each other and experimental results, as well as their computer run times and memory requirements, are noted.
Document ID
19850066863
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Petrie, S. L.
(Ohio State Univ. Columbus, OH, United States)
Freuler, R. J.
(Ohio State Univ. Columbus, OH, United States)
Gregorek, G. M.
(Ohio State Univ. Columbus, OH, United States)
Bragg, M. B.
(Ohio State University Columbus, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Meeting Information
Meeting: Aerospace simulation
Location: San Diego, CA
Start Date: February 2, 1984
End Date: February 4, 1984
Accession Number
85A49014
Funding Number(s)
CONTRACT_GRANT: NAS1-14406
Distribution Limits
Public
Copyright
Other

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