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Aerodynamic design methods for transonic wings*

Published online by Cambridge University Press:  04 July 2016

R. C. Lock
R. C. Lock*
Affiliation:
Centre for Aeronautics , The City University, London
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Summary

A review is given of current methods in theoretical aerodynamics which are useful in the design of aircraft wings for subsonic and transonic speeds. These are of two basic types:

  • (A) direct methods for calculating the flow over a givenwing shape. In the design process, these can be used to obtain a rapid estimate of the effect of a specified change in wing shape. The most practical methods of this type make use of the viscous/inviscid interaction technique; some recent methods are described and examples are given of their use, both in two and three dimensions, including comparisons with experiment.

  • (B) inverse methods in which the shape is calculated explicitly, as a result of either (a) specifying the surface pressure distribution on the wing, or (b) requiring that some suitable ‘target’ function, usually the drag/lift ratio, shall be a minimum. At present, these methods are restricted to inviscid flow.

Several examples of both ‘pressure’ and ‘optimisation’ methods are discussed, and their advantages and limitations considered.

Type
Research Article
Information
The Aeronautical Journal , Volume 94 , Issue 931 , January 1990 , pp. 1 - 16
Copyright
Copyright © Royal Aeronautical Society 1990 

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Footnotes

*

Based on a lecture given to the Royal Aeronautical Society on 1 April 1987.

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