John M. Riebe, Edwin E. Davenport
An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet-momentum-coefficient range was from 0 to 3.0 and the model angle of attack was 0 degrees.
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