Experimental Studies of Quasi-Two-Dimensional and Three-Dimensional Viscous Interaction Regions Induced by Skewed-Shock and Swept-Shock Boundary Layer Interactions
Abstract
This report describes results from 3 experimental studies designed to examine the aerothermal characteristics of regions of three-dimensional shock wave/boundary layer interaction in high-speed flow over non-adiabatic surfaces. The objectives were: (1) to explore the basic mechanisms associated with 3D boundary layer separation in high-speed flows with special emphasis on the large heat transfer rates and gradients developed in the separation and reattachment regions of these flows; and (2) to obtain detailed sets of experimental measurements with which to extend the simple semi-empirical prediction methods to the hypersonic/cooled wall regime where no previous data existed. These studies were conducted at mach 11 for Reynolds number of up to 40 million in Calspan's 96-Inch Shock Tunnel. In the first study we examined the effects of crossflow on the scale and properties of attached and separated region induced over a flate plate at the base of skewed/oblique shocks. Analysis of the detailed heat transfer and pressure measurements together with flow visualization demonstrated that, for sweep angles of up to 45 deg, crossflow had little effect on the size or characteristics of the interaction regions. In the second study the swept-shock was induced normal to the flat plate boundary layer by a shock generator mounted perpendicular to the flat plate. Our corner flow measurements demonstrated that, in highly-cooled hypersonic flows, the pressure rise to induce incipient separation is significantly larger than predicted by the semi-empirical methods.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1984
- Accession Number
- ADA150080
Entities
People
- M. S. Holden
Organizations
- Calspan