Accession Number : AD0692185

Title :   EXPERIMENTAL STUDY OF BOUNDARY-LAYER CONTROL BY BLOWING ON A FLAT PLATE FROM M = 2.5,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Grin,V. T.

Report Date : 03 FEB 1969

Pagination or Media Count : 7

Abstract : An experimental investigation of boundary layer control by the injection of gas through a two-dimensional slit in the region of shock wave-boundary layer interaction was carried out in wind tunnel with a closed test section. A gas is injected into a boundary layer in the direction of free flow. The experimental setup and measuring techniques are described briefly. The analysis of the experimental results shows that boundary layer control by gas injection makes it possible to raise the resistance of the boundary layer to separation, and that this may be achieved with a small expenditure of injected gas. (Author)

Descriptors :   (*BOUNDARY LAYER CONTROL, INJECTION), GAS FLOW, SHOCK WAVES, SUPERSONIC CHARACTERISTICS, TEST METHODS, FLOW SEPARATION, TURBULENT BOUNDARY LAYER, WEDGES, FLAT PLATE MODELS, WIND TUNNEL MODELS, REYNOLDS NUMBER, USSR

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE