Accession Number : AD0661992

Title :   SHOCK GENERATORS IN THE HYPERSONIC TURBULENT BOUNDARY LAYER.

Descriptive Note : Rept. for Jan 66-Jun 67,

Corporate Author : NEW YORK UNIV N Y SCHOOL OF ENGINEERING AND SCIENCE

Personal Author(s) : Gorman,Richard

Report Date : SEP 1967

Pagination or Media Count : 149

Abstract : In order to reduce the heat transfer and skin friction in a turbulent supersonic boundary layer, a totally immersed shock generator is employed. Values of wall heat transfer, skin friction, shock generator heat transfer and drag, and profiles of flow quantities downstream are obtained experimentally for several configurations. The boundary layer returns to a similar but thicker boundary layer within 20 boundary layer thicknesses downstream of the shock generator. Heat transfer and skin friction reductions of 8% to 27% are obtained. (Author)

Descriptors :   (*SHOCK WAVES, GENERATORS), (*TURBULENT BOUNDARY LAYER, HYPERSONIC CHARACTERISTICS), (*HYPERSONIC FLOW, *AERODYNAMIC HEATING), COOLING, HEAT TRANSFER, SKIN FRICTION, REDUCTION, DRAG, WAKE, DISSIPATION FACTOR, BOUNDARY LAYER, THICKNESS

Subject Categories : Aerodynamics
      Fluid Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE