Preliminary Investigation of the Shock-Boundary Layer Interaction in a Simulated Fan Passage
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1991
- Accession Number
- ADA242656
Entities
People
- Christopher C. Collins
Organizations
- Naval Postgraduate School