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Possible Types of Flow at Swept Leading Edges

Published online by Cambridge University Press:  07 June 2016

A. Stanbrook  and
L. C. Squiref
A. Stanbrook
Affiliation:
Royal Aircraft Establishment, Bedford
L. C. Squiref
Affiliation:
Royal Aircraft Establishment, Bedford
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Summary

Existing experimental data on the occurrence of attached flow around the leading edges of swept plane thin wings is summarised. It is shown that the change from separated to attached flow occurs while the Mach number normal to the leading edge is subsonic and that the Mach number required for the change increases with incidence. It is also shown that the Mach number and incidence conditions which hold on the boundaries dividing the two types of flow on wings with straight edges also apply locally at points on the leading edges of “Gothic” wings. The implications of this result on the flow over general curved-edge wings is briefly discussed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 15 , Issue 1 , February 1964 , pp. 72 - 82
Copyright
Copyright © Royal Aeronautical Society. 1964

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References

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