Addendum to a theoretical and experimental study of the boundary layer flow on a 45 degrees swept back wing

Date published

1957-11

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Publisher

College of Aeronautics, Cranfield

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Report

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Abstract

COA report 109 describes Flight Tests carried out on a swept back half wing of double elliptical section to investigate the nature of the boundary layer flow, with particular reference to Bounday Layer Instability and subsequent transition.

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Github

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Funder/s

M.O.S. contract No. 6/ Aircraft/14002/C.B.6 (a)

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