Effectiveness of boundary-layer control, obtained by blowing over a plain rear flap in combination with a forward slotted flap, in deflecting a slipstream downward for vertical take-off

Spreemann, Kenneth P
naca-tn-4200
Feb 1958


The wing employed in this investigation had a 67-percent-chord slotted flap in combination with a 33-percent-chord plain rear flap equipped with a full-span blowing nozzle. The tests were conducted in a static-thrust facility at the Langley Aeronautical Laboratory. The investigation indicated that the plain rear flap alone with a low momentum coefficient for boundary-layer control provided larger turning angles than the combined slotted and plain flaps without boundary-layer control.

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http://naca.central.cranfield.ac.uk/reports/1958/naca-tn-4200.pdf