Special bodies added on a wing to reduce shock-induced boundary-layer separation at high subsonic speeds

Richard T. Whitcomb
naca-tn-4293
Jun 1958


The effects of special bodies added on the upper surface of a wing to reduce shock-induced boundary-layer separation for lifting conditions at high subsonic speeds have been investigated. The basic test configuration had a relatively thick 35 degree sweptback wing of aspect ratio 7.05 mounted on a contoured fuselage.

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