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The Estimation of the Non-Linear Lift of Delta Wings at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

L. C. Squire
L. C. Squire*
Affiliation:
Department of Aeronautical Engineering, Queen's University, Belfast
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Summary:

Up to the present most of the methods used to calculate the flow over delta wings with leading edge separations have been based on slender wing theory. In this paper one of the simplest of these methods is carried over to linear theory and the overall lift calculated. In general the results are in agreement with experiment, in particular both show a fall in nonlinear lift as the leading edges of the wing approach the free stream Mach angles. The discrepancies which exist appear to arise mainly from the use of linear theory rather than from the mathematical model introduced to treat the separated flow.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 632 , August 1963 , pp. 476 - 480
Copyright
Copyright © Royal Aeronautical Society 1963

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References

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