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Boundary-Layer Flow Between the Attachment Lines on a Flat Plate Delta Wing at Incidence

Published online by Cambridge University Press:  07 June 2016

J. C. Cooke
J. C. Cooke*
Affiliation:
Royal Aircraft Establishment, Farnborough
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Summary

A three-dimensional laminar-boundary-layer calculation is carried out over the area concerned. The external flow is simplified, being calculated by slender-body theory assuming conical flow, with two point vortices above the wing, their positions and strength being determined by experiment. Attempts are made to draw transition fronts both for two-dimensional and sweep instability from this calculation. The combination of these gives fronts similar to those observed in some experiments. Because there is little or no pressure gradient over the area in question it is suggested that it is a region where distributed suction might usefully be applied in order to maintain laminar flow and reduce drag.

Type
Research Article
Information
Aeronautical Quarterly , Volume 13 , Issue 1 , February 1962 , pp. 1 - 16
Copyright
Copyright © Royal Aeronautical Society. 1962

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References

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