An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp

Shockwaves induce considerable flow separation loss; it is essential to reduce this using the flow control method. In this manuscript, a method for suppressing flow separation in turbomachinery through a constant adverse-pressure gradient was investigated. The first-passage shock was split into a co...

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出版年:	Applied Sciences
主要な著者:	Yongzhen Liu, Zhen Fan, Weiwei Cui, Qiang Zhou, Jianzhong Xu
フォーマット:	論文
言語:	英語
出版事項:	MDPI AG 2025-05-01
主題:	negative-curvature profile constant adverse-pressure gradient shockwave/boundary layer interaction supersonic compressor cascade
オンライン･アクセス:	https://www.mdpi.com/2076-3417/15/10/5664