TY - JOUR
T1 - Aerodynamic principles of shock-induced combustion ramjet engines
AU - Ma, Kaifu
AU - Zhang, Zijian
AU - Liu, Yunfeng
AU - Jiang, Zonglin
N1 - Funding Information:
This study is founded by the National Natural Science Foundation of China (No. 11672312 & No. 11532014 ).
Publisher Copyright:
© 2020 Elsevier Masson SAS
PY - 2020/8
Y1 - 2020/8
N2 - The shock-induced combustion ramjet engine is the most favorable air breathing propulsive system and a suitable option for high-speed flight. In this paper, theoretical analysis and numerical simulations were conducted to study the thrust performance of shock-induced combustion ramjet engines. Firstly, the propulsive performance of supersonic combustion ramjet engines was theoretically analyzed by using the Chapman-Jouguet detonation theory. Then, the aerodynamic principles of shock-induced combustion ramjet engines were put forth on the basis of the theoretical analysis results. Finally, a full-scale shock-induced combustion ramjet engine was designed according to the aerodynamic principles. Two-dimensional numerical simulations were conducted to simulate its combustion flow field and propulsive performance. The numerical results demonstrate the correctness and application of the theoretical aerodynamic principles.
AB - The shock-induced combustion ramjet engine is the most favorable air breathing propulsive system and a suitable option for high-speed flight. In this paper, theoretical analysis and numerical simulations were conducted to study the thrust performance of shock-induced combustion ramjet engines. Firstly, the propulsive performance of supersonic combustion ramjet engines was theoretically analyzed by using the Chapman-Jouguet detonation theory. Then, the aerodynamic principles of shock-induced combustion ramjet engines were put forth on the basis of the theoretical analysis results. Finally, a full-scale shock-induced combustion ramjet engine was designed according to the aerodynamic principles. Two-dimensional numerical simulations were conducted to simulate its combustion flow field and propulsive performance. The numerical results demonstrate the correctness and application of the theoretical aerodynamic principles.
KW - Chapman-Jouguet detonation
KW - Scramjet engines
KW - Shock-induced combustion ramjet engines
KW - Supersonic combustion
UR - http://www.scopus.com/inward/record.url?scp=85086066828&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2020.105901
DO - 10.1016/j.ast.2020.105901
M3 - Journal article
AN - SCOPUS:85086066828
SN - 1270-9638
VL - 103
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 105901
ER -