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An artificial viscosity method for the design of supercritical airfoilsA numerical technique is presented for the design of two-dimensional supercritical wing sections with low wave drag. The method is a design mode of the analysis code H which gives excellent agreement with experimental results and is widely used in the aircraft industry. Topics covered include the partial differential equations of transonic flow, the computational procedure and results; the design procedure; a convergence theorem; and description of the code.
Document ID
19790019965
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mcfadden, G. B.
(New York Univ. New York, NY, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-158840
COO-3077-158
Accession Number
79N28136
Funding Number(s)
CONTRACT_GRANT: NSG-1579
CONTRACT_GRANT: NGR-33-016-201
CONTRACT_GRANT: EY-76-C-02-3077
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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