Numerical Analysis of Turbulent Combustion Flow in HyShot Scramjet Engine

Author(s):  
Su-Hee Won ◽  
In-Seuck Jeung ◽  
Jeong-Yeol Choi ◽  
Vigor Yang ◽  
Fuhua Ma
2021 ◽  
Author(s):  
Le Tian ◽  
Haijun Sun ◽  
Yihua Xu ◽  
Ping Jiang ◽  
Hongyi Lu ◽  
...  

AIAA Journal ◽  
2013 ◽  
Vol 51 (7) ◽  
pp. 1566-1575 ◽  
Author(s):  
Hyo-Won Yeom ◽  
Bong-Gyun Seo ◽  
Hong-Gye Sung

2012 ◽  
Vol 452-453 ◽  
pp. 1334-1338
Author(s):  
De Song Liu ◽  
Hong Fu Qiang ◽  
Xue Li Xia ◽  
Guang Wang

The numerical simulation, based on computational fluid dynamics methodology, has been performed to study the two-phase turbulent combustion flow in rocket engine using non-metallized multicomponent propellant. A reduced reaction mechanism is developed for modelling combustion of fuel droplets in the absence of metal. Gas governing equations are two dimensional axisymmetric N-S equations in Eulerian coordinates. The trajectory model is adopted to analyse the droplet-phase including the droplet collision, breakup and evaporation. The gas flow is influenced by the droplets by adding source term to N-S equations. The reliability of the simulation programme is validated by comparing numerical simulation result with engine test data.


1998 ◽  
Author(s):  
Y. Igarashi ◽  
K. Nakahashi ◽  
M. Kodera ◽  
T. Mitani ◽  
T. Shimura

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