An Experimental Determination of the Unsteady Aerodynamics in a Controlled Oscillating Cascade

[+] Author and Article Information
S. Fleeter, A. S. Novick, R. E. Riffel, J. E. Caruthers

Detroit Diesel Allison Division, General Motors Corp., Indianapolis, Ind.

J. Eng. Power 99(1), 88-96 (Jan 01, 1977) (9 pages) doi:10.1115/1.3446257 History: Received December 11, 1976; Online July 14, 2010


A unique supersonic inlet flow field unsteady cascade experiment is described wherein the time-dependent pressure distribution within an harmonically oscillating airfoil cascade is quantitatively determined. The torsional frequency of oscillation and the inter-blade phase angle are precisely controlled by means of on-line digital computers. The dynamic data obtained include the chordwise distribution of the unsteady pressure magnitude and its phase lag as referenced to the airfoil motion. Parameters varied include the cascade inlet Mach number, the interblade phase angle, and the reduced frequency. The time-dependent data are correlated with state-of-the-art analytical predictions.

Copyright © 1977 by ASME
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