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

Vernard E. Lockwood, Raymond D. Vogler
naca-tn-4353
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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