Some Experimental Results of Two-Dimensional Compressor Cascades at Supersonic Inlet Velocities

[+] Author and Article Information
H. Starken, H. J. Lichtfuss

Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt, E. V., Institut für Luftstrahlantriebe, 505 Porz-Wahn, Germany

J. Eng. Power 92(3), 267-274 (Jul 01, 1970) (8 pages) doi:10.1115/1.3445351 History: Received December 08, 1969; Online July 14, 2010


The paper presents two-dimensional cascade results which have been obtained in transonic and supersonic cascade windtunnels. The upstream Mach number range is 1,0 ≤ M 1 ≤ 1,4. Tests have been carried out with three different blade shapes; these are double-circular-arc and wedge profiles. The influence of solidity on the performance of these cascades has been investigated. A detailed analysis and calculation of the shock losses shows the great influence of profile shape on the total pressure loss coefficient. The profile losses are roughly constant in the investigated Mach number range. In addition, some measurements for different back pressures are presented. These results are analyzed with the aid of a simple calculation, which shows that the axial velocity-density ratio has to be considered as an important parameter in supersonic cascade measurements.

Copyright © 1970 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