Effect of blade tip winglet on the performance of a highly loaded transonic compressor rotor

出版年份 2016 全文链接

标题

作者

关键词

Blade tip winglet, Numerical study, Shock wave/tip leakage vortex interaction, Stall range, Transonic compressor rotor

出版物

Volume 29, Issue 3, Pages 653-661

出版商

Elsevier BV

发表日期

2016-05-11

DOI

10.1016/j.cja.2016.04.014

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