Interaction of the Corner of Intersecting Wedges at a Mach Numer of 3 and High Reynolds Numbers.
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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The flow structure was determined in the streamwise corner formed by two intersecting wedges of 9 12-degree half angle in a supersonic stream at a Mach number of 3 and over a Reynolds number range from 40000 to 6 x 10 to the 7th power. Measurements included Pitot traverses, surface pressures, and oil flow visualization. For Reynolds numbers below 3000000 the wedge boundary layer was studied as laminar and transitional, with the corner interaction initially extended laterally well beyond the embedded shock. Spanwise surface pressure distributions for both the laminar and the turbulent cases are compared to those for two-dimensional flow separation.
- Fluid Mechanics