Accession Number:

ADA014742

Title:

Shock Wave Turbulent Boundary Layer Interaction in Hypersonic Flow

Descriptive Note:

Final rept. Mar 1972-May 1974

Corporate Author:

CALSPAN CORP BUFFALO NY

Personal Author(s):

Report Date:

1975-06-01

Pagination or Media Count:

186.0

Abstract:

A study is presented of the characteristics of transitional and turbulent layers, and regions of shock wave-turbulent boundary layer interaction in high Reynolds number hypersonic flow. An examination and correlation of skin friction, heat transfer and pressure measurements in laminar, transitional and turbulent boundary layers on sharp flat plates and cones are presented for the Mach range from 3 to 13 at wall-to-free stream temperature ratios from 0.1 to 0. 4.

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE