0
Research Papers

An Analysis of Axial Compressor Cascade Aerodynamics: Part II—Comparison of Potential Flow Results With Experimental Data

[+] Author and Article Information
G. L. Mellor

Princeton University, Princeton, N. J.

J. Basic Eng 81(3), 379-386 (Sep 01, 1959) (8 pages) doi:10.1115/1.4008480 History: Received August 08, 1958; Published September 01, 1959; Online February 20, 2019

Abstract

The theoretical potential flow results of Part I are compared with the large number of NACA 65-series compressor blade data. It is found that a single empirical constant used to modify the theory permits reasonable predictions of turning or lift coefficient to be made for any cascade geometry in the unstalled regions of flow. Furthermore, it is demonstrated that the theory allows a considerable number of plus and minus stalling angle of attack data to be collapsed to a single empirical curve. Conversely such a curve, once established, allows stalling predictions to be made for any cascade geometry. One interesting point on this curve is the loading limit above which the cascade is always stalled.

Copyright © 1959 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Related

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