scholarly journals Numerical investigation on shock train control and applications in a scramjet engine

2017 ◽  
Vol 60 ◽  
pp. 162-171 ◽  
Author(s):  
Fei Xing ◽  
Can Ruan ◽  
Yue Huang ◽  
Xiaoyuan Fang ◽  
Yufeng Yao
Keyword(s):  
Numerical Investigation ◽  
Shock Train ◽  
Train Control ◽  
Scramjet Engine

CFD Modeling of an Isolator Shock Train in a Scramjet Engine

2010 ◽  
Author(s):  
Troy Hoeger ◽  
Paul King ◽  
Douglas Decker ◽  
Jeffrey Donbar ◽  
Susan Cox-Stouffer
Keyword(s):  
Cfd Modeling ◽  
Shock Train ◽  
Scramjet Engine

Numerical investigation on the forced oscillation of shock train in hypersonic inlet with translating cowl

2019 ◽  
Vol 87 ◽  
pp. 311-322 ◽  
Author(s):  
Wen Shi ◽  
Juntao Chang ◽  
Junlong Zhang ◽  
Jicheng Ma ◽  
Ziao Wang ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Forced Oscillation ◽  
Shock Train ◽  
Hypersonic Inlet

Numerical investigation on behaviors of shock train in a hypersonic inlet with translating cowl

2018 ◽  
Vol 152 ◽  
pp. 682-691 ◽  
Author(s):  
Wen Shi ◽  
Juntao Chang ◽  
Junlong Zhang ◽  
Youyin Wang ◽  
Wenxin Hou ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Shock Train ◽  
Hypersonic Inlet

scholarly journals Numerical Investigation of Shock-Train Response to Inflow Boundary-Layer Variations

AIAA Journal ◽  
2017 ◽  
Vol 55 (9) ◽  
pp. 2888-2901 ◽  
Author(s):  
Romain Fiévet ◽  
Heeseok Koo ◽  
Venkat Raman ◽  
Aaron H. Auslender
Keyword(s):  
Boundary Layer ◽  
Numerical Investigation ◽  
Shock Train

Shock train control by boundary layer suction in a scramjet isolator

2020 ◽  
pp. 095441002096753
Author(s):  
Vignesh Ram Petha Sethuraman ◽  
Tae Ho Kim ◽  
Heuy Dong Kim
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Pressure Ratio ◽  
Critical Role ◽  
Pressure Rise ◽  
Flow Ratio ◽  
Shock Train ◽  
Boundary Layer Suction ◽  
Scramjet Engine ◽  
Suction Flow

The isolator plays a critical role in the scramjet engine situated between the inlet and the combustion chamber. The flow field is more complex with shock–shock interaction and shock boundary layer interaction result in a series of compression waves reffered to as “shock train”. The presence of such flow inside the isolator can degrade the performance of the scramjet engine. The present study focus on the characteristic of the shock train flow field in an isolator and its control by partial removal of the boundary layer. The results examine the variation of the inlet to outlet pressure ratio along with different suction flow ratio. Numerical results indicate that boundary layer suction will cause the slight downstream movement of shock train location and the length of the shock train is reduced. Also when the suction flow gets choked, the transformation of shock train into a single curved normal shock is observed. The effect of varying the upstream boundary layer plays a major role in the suction flow ratio. Furthermore, a significant improvement in the total pressure loss and static pressure rise is obtained by boundary layer suction. The location of the shock train has a greater impact on the performance of the isolator.

Sign in / Sign up

Export Citation Format

Share Document