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Rapid determination of aerodynamic sensitivity derivatives for subsonic wings

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 order perturbation panel method — is presented for calculating aerodynamic sensitivity derivatives for subsonic wings. The method is based on the low order panel method with the internal Dirichlet problem formulation and analytical differentiations cascaded and inverted. In terms of doublet strength sensitivity to configuration geometry, the computing cost of the present method for the partial derivative matrix calculation is less than one order of magnitude than the existing high order perturbation panel method, but the accuracy is comparable. Furthermore, by applying a physical interpolation instead of a weighted geometrical interpolation, the sensitivity derivatives of pressure, lift and pitching moment coefficient with respect to configuration geometry are derived and calculated in the present paper. Such sensitivity derivatives are lacking in high order perturbation panel method. A few calculative examples are given.

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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