Investigation of Small Surface Protuberances Up-Stream of Turbulent Boundary Layer Separation Produced by a Skewed Shock at Mach 3.
Interim rept. Jan-Feb 76,
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
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Tests were undertaken to determine the effect, if any, of a row of small sub-boundary layer-sized cylinders on a region of three-dimensional turbulent boundary layer separation produced by a skewed shock wave at a Mach number of 3. Surface oil flows and pressures showed no influence of the row of cylinders on the region of separation. Author
- Fluid Mechanics