Accession Number:

ADA179455

Title:

Theoretical Investigation of 3-D Shock Wave-Turbulent Boundary Layer Interactions. Part 5

Descriptive Note:

Final rept. 1 Oct 1985-30 Sep 1986

Corporate Author:

RUTGERS - THE STATE UNIV NEW BRUNSWICK NJ DEPT OF MECHANICAL INDUSTRIAL AND AEROSPACE ENGINEERING

Personal Author(s):

Report Date:

1987-02-24

Pagination or Media Count:

20.0

Abstract:

The research concerns the understanding of three dimensional shock wave turbulent boundary layer interactions. During the past year a collaborative effort has focused on theoretical and experimental investigations of the three dimensional swept compression corner at Mach 3 for compression angle of 24 deg sweep angle of 60 deg, and two different Reynolds numbers. The present author has computed the flowfield utilizing the three dimensional Reynolds averaged compressible Navier Stokes equations, with turbulence incorporated through the Baldwin Lomax algebraic turbulent eddy viscosity model. In separate efforts detailed experimental studies are performed on the flowfield, and the same configuration is computed using the Jones Launder turbulence model. The computed surface pressure profiles at the lower Reynolds number display significant disagreement with experiment. The computed surface pressure and boundary layer profiles of pitot pressure and yaw angle are in good agreement with experiment at the high Reynolds number. On the basis of detailed particle pathlines, the principal flowfield feature is observed to be a large vortical structure aligned approximately with the compression corner. This structure is qualitatively identical to the vortical structure observed for the three-dimensional sharp fin under the same external flow conditions.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE