Numerical solution of a problem involving the interaction of a shock wave with a cylinder in a supersonic flow

1971 ◽  
Vol 21 (6) ◽  
pp. 1518-1522 ◽  
Author(s):  
V. B. Balakin ◽  
V. V. Bulanov
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Numerical Solution

Experimental Research of Gasdynamic Liquid Drops Breakup in the Supersonic Flow with an Oblique Shock Wave

2020 ◽  
Author(s):  
K. Yu. Arefyev ◽  
O. V. Guskov ◽  
A. N. Prokhorov ◽  
A. S. Saveliev ◽  
E. E. Son ◽  
...  
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Experimental Research ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Liquid Drops

Evolution of weak shock wave in two-dimensional steady supersonic flow in dusty gas

2019 ◽  
Vol 160 ◽  
pp. 552-557 ◽  
Author(s):  
Rahul Kumar Chaturvedi ◽  
Pooja Gupta ◽  
L.P. Singh
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Weak Shock ◽  
Weak Shock Wave ◽  
Dusty Gas ◽  
Two Dimensional

Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave

Shock Waves ◽  
2012 ◽  
Vol 22 (6) ◽  
pp. 533-545 ◽  
Author(s):  
H. Yamauchi ◽  
B. Choi ◽  
K. Takae ◽  
T. Kouchi ◽  
G. Masuya
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Transverse Jet

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Jeyakumar Suppandipillai ◽  
Jayaraman Kandasamy ◽  
R. Sivakumar ◽  
Mehmet Karaca ◽  
Karthik K.
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Pressure Loss ◽  
Total Pressure ◽  
Injection Pressure ◽  
Total Pressure Loss ◽  
Normal Shock ◽  
Content Type ◽  
Normal Shock Wave ◽  
Scramjet Combustor

Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reported experiments. The results comply with the range, indicating the adopted simulation method can be extended for other investigations as well. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency and total pressure loss. Findings The results revealed that the augmentation of hydrogen jet pressure via variation in flame features increases the static pressure in the vicinity of the strut and destabilize the normal shock wave position. Indeed, the pressure of the mainstream flow drives the shock wave toward the upstream direction. The study perceived that once the hydrogen jet pressure is reached 4 bar, the incoming flow attains a subsonic state due to the movement of normal shock wave ahead of the strut. It is noticed that the increase in hydrogen jet pressure in the supersonic flow field improves the jet penetration rate in the lateral direction of the flow and also increases the total pressure loss as compared with the baseline injection pressure condition. Practical implications The outcome of this research provides the influence of fuel injection pressure variations in the supersonic combustion phenomenon of hypersonic vehicles. Originality/value This paper substantiates the effect of increasing hydrogen jet pressure in the reacting supersonic airstream on the performance of a scramjet combustor.

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