Design Method of Two-Step Hypersonic Mixed Compression Inlet in Condensability Segment for TBCC Engine
SHANG Xu-sheng 1,HE Yu-feng 2,LI Yin-guang 1,CAI Fei-chao 3
Journal of Propulsion Technology . 2015, (3): 365 -371 . 

Founded in 1980
Competent department: China Aerospace Science and Industry Group Co., Ltd
Sponsor: China Aerospace Science and industry group No.31 Research Institute
ISSN: 1001-4055
Journal of Propulsion Technology © 2021
E-mail: tjjs@sina.com
www.tjjscasic.com
Support: 010-62662699
Access Statistics

General Visit:

Visit Today:

Currently Online: