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A Note on the Vortex Patterns in the Boundary Layer Flow of a Swept-back Wing*

Published online by Cambridge University Press:  28 July 2016

Joseph Black
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Extract

Detailed investigations of the two-dimensional characteristics of thin aerofoil sections with small leading-edge radius have been made by Gault and McCullough. They found that at angles of incidence well below the stalling angle of the section, the laminar boundary layer separated from the surface near the nose, became transitional away from the surface, and re-attached to the aerofoil as a turbulent layer a little farther downstream. Beneath the separated layer, a “bubble” vortex was formed lying parallel to the leading edge, its rotation being such that the flow adjacent to the surface was towards the leading edge.

Type
Research Article
Information
The Aeronautical Journal , Volume 56 , Issue 496 , April 1952 , pp. 279 - 285
Copyright
Copyright © Royal Aeronautical Society 1952

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Footnotes

*

Unexpected behaviour of the boundary layer flow pattern was found by the author during a recent experimental investigation on a swept-back wing. The photographs indicate that this pattern is different from that which has been generally accepted in the past few years. The work is to be written up at length, but it was considered important that this information should be made known quickly.

References

1. Gault, D. E. (1949). Boundary Layer and Stalling Characteristics of the N.A.C.A. 63-009 Airfoil Section. N.A.C.A. Technical Note 1894, June 1949.Google Scholar
2. McCullough, G. B. and Gault, D. E. (1949). Boundary Layer and Stalling Characteristics of . the N.A.C.A. 64 A 006 Airfoil Section. N.A.C.A. Technical Note 1923, August 1949.Google Scholar