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...

Full description

Saved in:

Bibliographic Details
Main Author:	Austin, Jeffrey G
Format:	Report
Language:	eng
Subjects:	BOUNDARY LAYER FLOW CASCADES(FLUID DYNAMICS) FAN BLADES FLOW FIELDS Fluid Mechanics MACH NUMBER PRESSURE GRADIENTS SHOCK BOUNDARY LAYER INTERACTIONS SHOCK WAVES STATIC PRESSURE THESES TRANSONIC FLOW VORTEX GENERATORS WAKE
Online Access:	Request full text
Tags:	Add Tag No Tags, Be the first to tag this record!

Description
Summary:	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 program consisted of the design and calibration of a traversing three-port pneumatic probe to measure Mach number and flow angle and initial cascade measurements to provide baseline data for the fully-mixed-out total pressure loss coefficient and flow turning angle. Similar tests are planned with the vortex generating devices installed. Comparisons with and without the vortex generating devices are needed to quantify the overall effect on the shock-boundary interaction in a transonic fan-blade passage, and to assess the potential for using vortex generating devices in military engine fans.