Numerical Computation of Nonstationary Aerodynamics of Flat Plate Cascades in Compressible Flow

[+] Author and Article Information
R. H. Ni

Pratt & Whitney Aircraft, East Hartford, Ct.

F. Sisto

Mechanical Engineering Department, Stevens Institute of Technology, Castle Point Station, Hoboken, N.J.

J. Eng. Power 98(2), 165-170 (Apr 01, 1976) (6 pages) doi:10.1115/1.3446132 History: Received November 22, 1974; Online July 14, 2010


The “time marching” technique is successfully applied to the numerical computation of the nonstationary aerodynamics of a flat plate cascade for compressible flow of either subsonic or supersonic nature. The unsteady perturbation amplitudes of fluid properties are used as the dependent variables so that the computational domain can be reduced to a two-dimensional channel guided by two adjacent blades for any interblade phase angle. A new method of handling the boundary condition is developed in which the order of accuracy for the boundary points will be the same as the interior points. The wake region behind the trailing edge of each blade is treated as a “slip plane” as done in two-dimensional steady state supersonic flow. Results are in good agreement with existing analytical solutions.

Copyright © 1976 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