An Analytic and Experimental Study of the Effects of Splitter Plate Position on the Trailing Edge Modifications of a Cambered 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 on trailing edge modifications of a circulation controlled airfoil. Analytic studies were conducted to determine the feasibility of using a potential flow computer program to predict the results of the wind tunnel tests. The airfoil model was elliptical in shape, 20 percent thick, and had five percent camber. It employed a blowing slot for circulation control and a splitter plate for reduction in mixing losses. Modifications included slot positions on the upper surface of 96 and 97 percent chord, slot angles of 5 and -33 degrees, circular and elliptic aft contours, and splitter plate positions on the lower surface of 99 and 95.3 percent chord. Tests were conducted at a Reynolds number of 740 thousand and blowing momentum coefficients of zero and 0. 03.
- Fluid Mechanics