A fast computational method of the aerodynamic performance of fan and booster with inlet distortion
Author:
Affiliation:
1. Shanghai Jiao Tong University, Shanghai, China
2. AECC Hunan Aviation Powerplant Research Institute, Zhuzhou, China
3. Key Laboratory (Fluid Machinery and Engineering Research Base) of Sichuan Province, China
Abstract
Publisher
SAGE Publications
Subject
Mechanical Engineering
Link
http://journals.sagepub.com/doi/pdf/10.1177/09544062221115346
Reference35 articles.
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5. An Actuator Disc Analysis of Inlet Distortion and Rotating Stall in Axial Flow Turbomachines
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