Accession Number : AD0763468

Title :   Experimental Investigation of Wake Velocity Fluctuations Behind Stalled Wings at Reynolds Numbers up to 4.8 Million.

Descriptive Note : Final rept. Feb 71-Feb 73,

Corporate Author : ALLIED RESEARCH ASSOCIATES INC NEWTON UPPER FALLS MASS

Personal Author(s) : Smiley,Robert F.

Report Date : FEB 1973

Pagination or Media Count : 61

Abstract : 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)

Descriptors :   (*AIRFOILS, WAKE), STALLING, VORTICES, BUFFETING, ANGLE OF ATTACK, WIND TUNNEL MODELS

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE