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):

Report Date:

1967-09-01

Pagination or Media Count:

149.0

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

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE