A Wind Tunnel Study of the Effects of Trailing Edge Modifications on the Lift-Drag Ratio of a Circulation Controlled 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 trailing edge modifications on the lift-to-drag ratio of a circulation controlled airfoil. The model was a 20 percent thick, five percent cambered, elliptical airfoil. The airfoil was modified in aft contour, blowing slot position, and blowing angle. A 1.5 inch splitter plate was mounted at the 99 percent chord for all tests. The tests were run at a Reynolds Number, based on model chord, of 741,000, while the angle of attack and blowing rate were varied during each test sequence.
- Fluid Mechanics