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The Estimation of Pressure on Finite Symmetrical Wings in Subsonic Flow

Published online by Cambridge University Press:  07 June 2016

R. H. Eldridge  and
F. Walkden
R. H. Eldridge
Affiliation:
Department of Mathematics, University of Saltord
F. Walkden
Affiliation:
Department of Mathematics, University of Saltord
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Summary

A numerical method for estimating the pressure distribution on arbitrary finite symmetrical wings with rounded leading edges at zero incidence in subsonic flow is presented. The subsonic flow equations are linearised so that the value of ∂ϕ/∂x at a point on the wing mean plane can be expressed as the generalised principal part of a singular double integral. This integral is modified so that it can be evaluated numerically. Finally Cn is obtained from ∂ϕ/∂x by using the approximation Cp = −2∂ϕ/∂x. Two numerical methods are described; one method to be used when the field point is close to the leading edge and the other for field points in other regions. Numerical results for two wings (Warren 12 and NPL 55° swept) are given and, wherever possible, the computed results are compared with results from other methods and with experiment.

Type
Research Article
Information
Aeronautical Quarterly , Volume 22 , Issue 1 , February 1971 , pp. 65 - 82
Copyright
Copyright © Royal Aeronautical Society. 1971

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