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A linearized theory method of constrained optimization for supersonic cruise wing designA linearized theory wing design and optimization procedure which allows physical realism and practical considerations to be imposed as constraints on the optimum (least drag due to lift) solution is discussed and examples of application are presented. In addition to the usual constraints on lift and pitching moment, constraints are imposed on wing surface ordinates and wing upper surface pressure levels and gradients. The design procedure also provides the capability of including directly in the optimization process the effects of other aircraft components such as a fuselage, canards, and nacelles.
Document ID
19770011054
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Carlson, H. W. (NASA Langley Research Center Hampton, VA, United States)
Middleton, W. D. (Boeing Commercial Airplane Co. Seattle, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Publication Information
Publication: Proc. of the SCAR Conf., Part 1
Subject Category
Aircraft Design, Testing And Performance
Accession Number
77N17998
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19770011052Collected WorksProceedings of the SCAR Conference, Part 1
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