Three-Dimensional Swept Shock/Turbulent Boundary-Layer Separations with Control by Air Injection,
NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO)
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Experimentally determined wall pressure distributions, local surface shear stresses and their directions, and detailed turbulent boundary-layer traverses in near zero heat transfer conditions, are presented through skewed shockboundary-layer interaction regions generated by a wedge standing normal to a test wall. The mainstream Mach numbers were 2 and 4, while the Reynolds number based on the undisturbed test boundary-layer thickness of 0.2-in., growing along the nozzle sidewall of the NAE 5 X 5-in. blowdown wind tunnel, was 200,000. Tangential air injection at a jet exit Mach number of 3 was then introduced into the 3D shock separated Mach 2 boundary layer, to control the separation. The optimum direction of blowing was found to be along a line somewhere between the deflected surface of the wedge and the line of the oblique shock wave.
- Fluid Mechanics