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Rapid determination of aerodynamicsensitivity derivatives for subsonicwings

Published online by Cambridge University Press:  04 July 2016

X. Mingchu  and
G. Wenying
X. Mingchu
Affiliation:
Northwestern Polytechnical University, Xi'an, People's Republic of China
G. Wenying
Affiliation:
Northwestern Polytechnical University, Xi'an, People's Republic of China
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Summary

A rapid quasi-analytical method — low orderperturbation panel method — is presented forcalculating aerodynamic sensitivity derivatives forsubsonic wings. The method is based on the low orderpanel method with the internal Dirichlet problemformulation and analytical differentiations cascadedand inverted. In terms of doublet strengthsensitivity to configuration geometry, the computingcost of the present method for the partialderivative matrix calculation is less than one orderof magnitude than the existing high orderperturbation panel method, but the accuracy iscomparable. Furthermore, by applying a physicalinterpolation instead of a weighted geometricalinterpolation, the sensitivity derivatives ofpressure, lift and pitching moment coefficient withrespect to configuration geometry are derived andcalculated in the present paper. Such sensitivityderivatives are lacking in high order perturbationpanel method. A few calculative examples aregiven.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 994 , April 1996 , pp. 121 - 134
Copyright
Copyright © Royal Aeronautical Society 1996 

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