Accession Number:

ADA411523

Title:

Exploratory Experimental Study of Transitional Shock Wave Boundary Layer Interactions

Descriptive Note:

Final rept. 1 Jan-31 Oct 2002

Corporate Author:

TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Personal Author(s):

Report Date:

2003-01-31

Pagination or Media Count:

11.0

Abstract:

An exploratory investigation has been made of transitional shock wave boundary layer interactions. In this case, the interaction is induced by a circular cylinder perpendicular to a flat plate. The tests were conducted in the Mach 5 blowdown tunnel of The University of Texas at Austin. The primary goal of this initial, exploratory study was to determine if repeatable transitional interactions could be generated. Measurements included surface flow visualization using the kerosene-lampblack technique and high speed schlieren imaging. Consistent with earlier experiments the current work shows that as the cylinder is shifted upstream on the plate and the interaction start moves into an area where the incoming boundary layer is transitional, rather than turbulent, the separated flow and overall interaction scales increase significantly.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE