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.
A Wind Tunnel Study of the Effects of Trailing Edge Modifications on the Lift-Drag Ratio of a Circulation Controlled Airfoil
1975
68 pages
Report
No indication
English
Aerodynamics , Fluid Mechanics , Aircraft , Lift to drag ratio , Aerodynamic control surfaces , Wind tunnel tests , Circulation , Boundary layer control , Trailing edges , Modification , Ellipsoids , Theses , Airfoils , High lift , Flow rate , Measurement , Pitot tubes , Circulation controlled airfoils , Elliptical airfoils
Wind tunnel pressure distribution tests on an airfoil with trailing edge flap
Engineering Index Backfile | 1929
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