Computation of the Detached Shock and the Entrance Flow Field in a Supersonic or Transonic Cascade FREE

[+] Author Affiliations
Hua Yaonan

Chinese Academy of Sciences, Beijing, China

Paper No. 85-GT-7, pp. V001T03A006; 8 pages
  • ASME 1985 International Gas Turbine Conference and Exhibit
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 18–21, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7938-2
  • Copyright © 1985 by ASME


A method is presented in this paper for determining the shape of the detached shock and flow field quantities in the supersonic entrance region on an arbitrary stream surface of revolution. The equation of characteristics and the corresponding equation of compatibility are derived. The shape of the detached shock obtained is taken as the initial-value curve to calculate the supersonic entrance region by means of the method of characteristics. Consequently, the unique inlet flow angle is also calculated. Typical computations show that this method is both effective and rapid.

Copyright © 1985 by ASME
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