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Measurement of Downwash at a Mach Number of 1.45 Behind Two Wings of Finite Span

Published online by Cambridge University Press:  28 July 2016

W. F. Hilton
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Abstract

Measurements were made of the downwash effects behind two finite wings 3.1 percent, thick, having square and 20° raked tips respectively. The tests were conducted at a Mach number of 1.45 and a Reynolds number of 1.2 millions by traversing a yawmeter 1.62 chords behind the trailing edge of the finite wings.

In general, a maximum downwash of the order of ½° per degree of wing incidence was observed in that portion of the tip Mach cone behind the wing, and a maximum upwash of similar magnitude was observed in that part of the tip Mach cone situated outboard of the wing.

Thus it is apparent that these effects are large enough to affect the lift on any surface situated in the tip Mach cone behind a finite wing. In particular, placing the rear surface in the downwash region behind a finite wing, will tend to reduce the overall lift while placing it in the upwash region will tend to magnifiy the variations of lift initiated by the finite wing.

Type
Research Article
Information
The Aeronautical Journal , Volume 55 , Issue 481 , January 1951 , pp. 43 - 51
Copyright
Copyright © Royal Aeronautical Society 1951

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References

1. Lighthill, M. J. Two-dimensional Supersonic Aerofoil Theory. R.&M. 1929 (1944).Google Scholar
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3. Lagerstrom, P. A. and Graham, M. E., Downwash and Sidewash Problems in Supersonic Wing Theory, Engineering Review, Sept.1947.Google Scholar
4. Hilton, W. F. High Speed Aerodynamics. (In the press.)Google Scholar