Shock wave end wall boundary layer interaction in a transonic compressor rotor
The passage shock wave end wall boundary layer interaction in a transonic compressor was investigated with a laser transit anemometer. A two stage transonic compressor designed without inlet guide vanes was used in this flow field investigation. Measurements of the flow velocity were made within the...
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Virginia Polytechnic Institute and State University
2014
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| Online Access: | http://hdl.handle.net/10919/49872 |