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Methods of Reducing the Transonic Drag of Swept - Back Wings at Zero Lift*

Published online by Cambridge University Press:  28 July 2016

D. Küchemann
D. Küchemann*
Affiliation:
Royal Aircraft Establishment, Farnborough
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Extract

The purpose of this paper is to review briefly some means of reducing the normal-pressure drag at transonic speeds of wings and wing-body combinations without lift. By transonic speeds is meant here not only the range of main stream Mach numbers around unity but, more generally, that speed range where a transonic type of flow around the body may exist. Thick non-lifting bodies as are considered here cause a displacement flow and it may be recalled that at least three different types of flow are involved: a subsonic, a transonic, and a supersonic type of flow, all of which are here assumed to have one attachment line along the leading edge and one separation line along the trailing edge. This excludes types of flow where separations occur elsewhere, such as shock-induced separations along some line within the wing chord.

Type
Research Article
Information
The Aeronautical Journal , Volume 61 , Issue 553 , January 1957 , pp. 37 - 42
Copyright
Copyright © Royal Aeronautical Society 1957

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Footnotes

*

This paper was given at the Ninth International Congress of Applied Mechanics, Brussels in 1956. Only a short abstract will be published in the Congress Proceedings.

References

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