Preliminary Investigation of the Shock-Boundary Layer Interaction in a Simulated Fan Passage
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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A two dimensional, two passage simulation of the relative flow through a transonic fan at M 1.4 was designed with a view to providing an apparatus in which to assess the effectiveness of passive vortex generator techniques in alleviating shock-boundary layer interaction effects. The design of the model and the results of six test runs in the transonic cascade blowdown wind tunnel are described. Schlieren photographs of the shock structure were obtained at back pressures lower than the design value. The back-pressure control valve was identified as being critical to completing the experimental simulation. The flow through the cascade geometry was computed at design pressure ratio using an Euler code. Modifications to the grid are recommended before thin-layer Navier-Stokes calculations are performed.
- Fluid Mechanics