Accession Number : ADA191544
Title : Computation of the Turbulent Boundary Layer Downstream of Vortex Generators.
Descriptive Note : Final rept. Sep 86-Sep 87,
Corporate Author : DAVID TAYLOR RESEARCH CENTER BETHESDA MD
Personal Author(s) : Chang, Paul K
PDF Url : ADA191544
Report Date : Dec 1987
Pagination or Media Count : 47
Abstract : The approximate analysis of three-dimensional incompressible turbulent boundary layer downstream of vortex generators is presented. Extensive numerical computations are carried out to assess the effectiveness of single-row, counter-rotating vane-type vortex generators to alleviate flow separation lines. Flow separation downstream of the vortex generators on a thick airfoil are determined in terms of size, location, and arrangement of the vortex generators. These lines are compared with the separation line without the vortex generators. High efficiency is obtained with the moderately slender rectangular blade of the generator. The results indicate that separations is alleviated more effectively in the region closer to the symmetry axis of the generator than in the outer region of the symmetry axis. No optimum conditions for the alleviation of flow separation are established in this investigation, and no comparisons are made with other analytical results and experimental data. Keywords: Boundary layer computations, Flow separation, Vortex generators.
Descriptors : *VORTEX GENERATORS, *FLOW SEPARATION, *TURBULENT BOUNDARY LAYER, FLOW SEPARATION, REDUCTION, BOUNDARY LAYER, COMPUTATIONS, EXPERIMENTAL DATA, EFFICIENCY, HIGH RATE, NUMERICAL ANALYSIS, SEPARATION, SYMMETRY, APPROXIMATION(MATHEMATICS), MATHEMATICAL ANALYSIS, SIZES(DIMENSIONS), OPTIMIZATION, BLADES, RECTANGULAR BODIES, SLENDER BODIES, AIRFOILS, JET FLOW, INCOMPRESSIBLE FLOW, VORTEX GENERATORS
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE