Accession Number : AD0762077
Title : Wind Tunnel Tests of a Trapped Vortex-High Lift Airfoil.
Descriptive Note : Final rept. 23 Feb-23 Dec 72,
Corporate Author : ADVANCED TECHNOLOGY CENTER INC DALLAS TEX
Personal Author(s) : Krall,K. M. ; Haight,C. H.
Report Date : 23 DEC 1972
Pagination or Media Count : 60
Abstract : Two dimensional low speed wind-tunnel tests have demonstrated the feasibility of employing trapped vortex diffusion on a high lift airfoil configuration. All 11 percent supercritical airfoil was selected as the base contour employing both leading and trailing edge flaps. The leading edge flap was 25 percent chord, drooped 30 degrees with the rear flap, 27 percent chord, deflected 15 degrees and 30 degrees. Trapped vortex cavities, affording boundary layer control with rapid diffusion, are located at each of the flap knees. Because of the high trapped vortex efficiency, blowing requirements are minimal. Section lift coefficients, in excess of 6, were achieved in the test. (Modified author abstract)
Descriptors : (*AIRFOILS, BOUNDARY LAYER CONTROL), (*SHORT TAKEOFF AIRCRAFT, LIFT), VORTEX GENERATORS, WIND TUNNEL MODELS, DRAG, PITCH(MOTION), AERODYNAMIC SLOTS, VORTICES, FEASIBILITY STUDIES
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE