Experimental Investigation of Wake Velocity Fluctuations Behind Stalled Wings at Reynolds Numbers up to 4.8 Million.
Final rept. Feb 71-Feb 73,
ALLIED RESEARCH ASSOCIATES INC NEWTON UPPER FALLS MASS
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A wind tunnel investigation was made of transient wake velocities behind three stalled wings with NACA 0012 airfoils and spans equal to test section width up to a maximum Reynolds number of 4.8 million. Two wings had constant chords of 6 inches and 3 inches and one was tapered with a root chord of 12 inches and a tip chord of 6 inches. Anemometer time-history data were recorded on tape for angles of attack of 16.2 degrees, 21.1 degrees, 25.8 degrees and 30.3 degrees, and were used to evaluate wake geometry, frequency and mean and perturbation velocities for the constant chord wings. Modified author abstract
- Fluid Mechanics