Exploratory wind-tunnel investigation at high subsonic and transonic speeds of jet flaps on unswept rectangular wings

Vernard E. Lockwood, Raymond D. Vogler
Aug 1958

An investigation has been made in the Langley high-speed 7- by 10-foot tunnel by means of the transonic-bump technique to determine the lift augmentation of several jet-flap configurations. Thrust-recovery characteristics of some of the thick-wing configurations were also determined. The investigation covered a Mach number range from 0.40 to 1.10, and a maximum momentum coefficient of 0.30 was obtained at a Mach number of 0.40

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