Accession Number:

ADA083703

Title:

Investigation of Three-Dimensional Shock Wave Boundary Layer Interactions. A Flow-Field Model of the Glancing Shock/Turbulent Boundary Layer Interaction.

Descriptive Note:

Final scientific rept. Jun 76-Oct 79,

Corporate Author:

COLLEGE OF AERONAUTICS CRANFIELD (ENGLAND)

Personal Author(s):

Report Date:

1980-01-01

Pagination or Media Count:

243.0

Abstract:

Three-dimensional glancing-shockturbulent boundary-layer interaction has been investigated at the Cranfield Institute of Technology in two separate test programmes using a 2.5 x 2.5 inch intermittent tunnel and a 9 x 9 inch continuous tunnel, at a Mach number of approximately 2.5. The experimental results include oil-flow pictures, vapour-screen photographs, surface static pressure distributions, local heat transfers, liquid crystal pictures of surface temperature, and viscous layer surveys. The test data indicate that the interaction region consists of two different viscous flows, the side-wall boundary layer and an induced layer originating near the shock generator root and crossing the path of the side-wall boundary layer. In this flow field model, no flow separation appears as long as the surface stream lines of the side-wall boundary layer can be pliable enough to be bent along the edge of the induced layer, even when the surface-flow deflection exceeds the shock angle. However, an ordinary separation does take place when the induced layer forces the surface stream lines to deflect beyond a maximum permissible angle. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE