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...
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 |
Similar Items
-
The effects of low-profile vortex generators on flow in a transonic fan-blade cascade
by: Gamerdinger, Peter M.
Published: (2012) -
On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades
by: Marcel Boerner, et al.
Published: (2018-10-01) -
Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade
by: Lepicovsky J., et al.
Published: (2004-01-01) -
Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade
by: J. Lepicovsky, et al.
Published: (2004-01-01) -
The effect of blade solidity on the aerodynamic loss of a transonic turbine cascade
by: Doughty, Roger L.
Published: (2014)