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Airfoil design method using the Navier-Stokes equationsAn airfoil design procedure is described that was incorporated into an existing 2-D Navier-Stokes airfoil analysis method. The resulting design method, an iterative procedure based on a residual-correction algorithm, permits the automated design of airfoil sections with prescribed surface pressure distributions. The inverse design method and the technique used to specify target pressure distributions are described. It presents several example problems to demonstrate application of the design procedure. It shows that this inverse design method develops useful airfoil configurations with a reasonable expenditure of computer resources.
Document ID
19910053927
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Malone, J. B.
(NASA Langley Research Center Hampton, VA, United States)
Narramore, J. C.
(Bell Helicopter Textron, Inc. Fort Worth, TX, United States)
Sankar, L. N.
(Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
March 1, 1991
Publication Information
Publication: Journal of Aircraft
Volume: 28
ISSN: 0021-8669
Subject Category
Aircraft Design, Testing And Performance
Accession Number
91A38550
Distribution Limits
Public
Copyright
Other

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