Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence

[+] Author and Article Information
Y. Elazar, R. P. Shreeve

Turbopropulsion Laboratory, Department of Aeronautics and Astronautics, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 112(2), 256-265 (Apr 01, 1990) (10 pages) doi:10.1115/1.2927642 History: Received January 17, 1989; Online June 09, 2008


A detailed two-component LDV mapping of the flow through a controlled diffusion compressor cascade at low Mach number ( ~ 0.25) and Reynolds number of about 7 × 105 , at three inlet air angles from design to near stall, is reported. It was found that the suction-side boundary layer reattached turbulent after a laminar separation bubble, and remained attached to the trailing edge even at the highest incidence, at which losses were 3 to 4 times the minimum value for the geometry. Boundary layer thickness increased to fill 20 percent of the blade passage at the highest incidence. Results for pressure-side boundary layer and near-wake also are summarized. Information sufficient to allow preliminary assessment of viscous codes is tabulated.

Copyright © 1990 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In