An Experimental Investigation of Loss Reduction With Riblets on Cascade Blade Surfaces and Isolated Airfoils PUBLIC ACCESS

[+] Author Affiliations
Chen Fang

Chinese Academy of Science, Beijing, China

Tang Yan-Ping, Chen Mao-Zhang

Beijing University of Aeronautics and Astronautics, Beijing, China

Paper No. 90-GT-207, pp. V001T01A060; 6 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


Experimental investigations of loss reduction with riblets have been made. Riblets were put on the blade surfaces in different ways in a compressor cascade or on an isolated airfoil. More than 8% drag reduction benefits for an isolated airfoil and more than 10% loss reduction benefits for the compressor cascade have been obtained by using riblets only on blade pressure surfaces rather than on both pressure and suction surfaces. The mechanism underlying these results has been discussed.

Copyright © 1990 by ASME
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