Mach number, flow angle, and loss measurements downstream of a transonic fan-blade cascade
Two dimensional flow measurements of Mach number and flow angle were conducted downstream of a transonic fan-blade cascade at a mach number of 1.4 to provide baseline data for assessing the effect of vortex generating devices on the suction surface shock-boundary layer interaction. The experimental...
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| Language: | en_US |
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Monterey, California. Naval Postgraduate School
2013
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| Online Access: | http://hdl.handle.net/10945/30868 |