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Wind-tunnel Investigation of Stall Control by Suction Through a Porous Leading Edge on a 37 Degree Sweptback Wing of Aspect Ratio 6 at Reynolds Numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)

Robert Graham, William A Jacques

Abstract

Report presenting an investigation of the effects of suction through a porous leading-edge surface in the 19-foot pressure tunnel on a wing with 37 degrees of sweepback of the leading edge, an aspect ratio of 6, taper ratio of 0.5, and NACA 64(sub 1)-212 airfoil sections normal to the 27-percent-chord line. Results regarding the wing without flaps, wing with trailing-edge flaps, and power requirements for porous-leading-edge suction are provided.

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Key concepts: Stall (fluid mechanics), Airfoil, Wing, Leading edge, Trailing edge, Reynolds number, Chord (peer-to-peer), Wind tunnel