A Wind Tunnel Study of the Effects of Splitter Plate Position and Angle on the Lift-Drag Ratio of a Circulation Controlled Elliptical Airfoil
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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Wind tunnel tests were conducted to determine the effects of splitter plate position and angle on the lift-to-drag ratio of a circulation controlled airfoil. The model was a 20 percent thick, five percent cambered elliptical airfoil, with a blowing slot for circulation control located at the 96 percent chord position on the upper surface. A splitter plate of 1.5-in. chord was mounted on the lower aft surface of the airfoil in five different test configurations. The tests were run at a constant Reynolds number, based on the model chord, of 770,000, while the angle of attack and the secondary blowing were varied at each test increment.