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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Bibliographic Details
Main Author: Austin, Jeffrey G.
Other Authors: Shreeve, Raymond P.
Language:en_US
Published: Monterey, California. Naval Postgraduate School 2013
Online Access:http://hdl.handle.net/10945/30868

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