THEORETICAL AND EXPERIMENTAL STUDIES OF THE SHOCK WAVE-BOUNDARY LAYER INTERACTION ON COMPRESSION SURFACES IN HYPERSONIC FLOW
Final rept. Nov 1966-Nov 1969
CORNELL AERONAUTICAL LAB INC BUFFALO NY
Pagination or Media Count:
A detailed description is given of the theoretical and experimental studies of shock wave-laminar boundary layer interaction on curved compression surfaces in hypersonic flow. Integral forms of the boundary layer equations were used for the conservation of mass, streamwise momentum, normal momentum, moment of streamwise momentum and energy to describe the development of attached and separated boundary layers on a curve surface. In the experimental study, skin friction, heat transfer and pressure measurements were made on a series of flat plate-cylindrical arc-wedge compression surfaces. Pitot and cone pressure measurements were made above the surface in the separation and reattachment regions of separated flows to estimate the static pressure difference across the boundary layer. The radius of curvature of the cylindrical arc, the inclination of the wedge, and the unit Reynolds number of the free-stream were varied to examine their effect on the properties of both attached and separated interaction regions over the models.
- Guided Missile Reentry Vehicles
- Fluid Mechanics