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Application of numerical optimization to the design of advanced supercritical airfoilsAn application of numerical optimization to the design of advanced airfoils for transonic aircraft showed that low-drag sections can be developed for a given design Mach number without an accompanying drag increase at lower Mach numbers. This is achieved by imposing a constraint on the drag coefficient at an off-design Mach number while minimizing the drag coefficient at the design Mach number. This multiple design-point numerical optimization has been implemented with the use of airfoil shape functions which permit a wide range of attainable profiles during the optimization process. Analytical data for the starting airfoil shape, a single design-point optimized shape, and a double design-point optimized shape are presented. Experimental data obtained in the NASA Ames two-by two-foot wind tunnel are also presented and discussed.
Document ID
19790011878
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, R. R. (Vought Corp. Moffett Field, CA, United States)
Hicks, R. M. (NASA Ames Research Center)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Publication Information
Publication: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1
Subject Category
Aerodynamics
Accession Number
79N20049
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19790011859Collected WorksAdvanced Technology Airfoil Research, volume 1, part 1
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