23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-2.10.5

FLOW CONTROL OVER THE WING OF A FIGHTER-TYPE CONFIGURATION USING BOUNDARY LAYER SUCTION

M. R. Soltani, T. Khadivi, A. R. Davari
Sharif University of Technology, Iran

Keywords: cropped delta wing, vortex, flow control, suction, sweep angle

Effectiveness of an active suction technique to delay separation over a 40-degree swept cropped delta wing is experimentally studied at subsonic speeds and low to moderate angles of attack. Pressure measurements and flow visualization indicate formation of a vortex on the wing, which expands and then disappears as the angle of attack is increased. Effect of suction on the velocity profiles is noticeable at low angles of attack and diminishes as alpha is increased.

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