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Numerical optimization design of advanced transonic wing configurations

Author
Holst, T. L.
Published
May 1, 1984.
Physical Description
1 electronic document
Additional Creators
Cosentino, G. B.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
A computationally efficient and versatile technique for use in the design of advanced transonic wing configurations has been developed. A reliable and fast transonic wing flow-field analysis program, TWING, has been coupled with a modified quasi-Newton method, unconstrained optimization algorithm, QNMDIF, to create a new design tool. Fully three-dimensional wing designs utilizing both specified wing pressure distributions and drag-to-lift ration minimization as design objectives are demonstrated. Because of the high computational efficiency of each of the components of the design code, in particular the vectorization of TWING and the high speed of the Cray X-MP vector computer, the computer time required for a typical wing design is reduced by approximately an order of magnitude over previous methods. In the results presented here, this computed wave drag has been used as the quantity to be optimized (minimized) with great success, yielding wing designs with nearly shock-free (zero wave drag) pressure distributions and very reasonable wing section shapes.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19840019650.
Accession ID: 84N27718.
NASA-TM-85950.
A-9725.
NAS 1.15:85950.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15707605