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Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing

Arvid L. Keith

出版	National Advisory Committee for Aeronautics, 1950
URL	http://books.google.com.hk/books?id=r0rLdXE7G44C&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋

Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.