scholarly journals Interaction of Reflected Shock Wave with Shock Tube Wall

2004 ◽  
Vol 52 (603) ◽  
pp. 153-159 ◽  
Author(s):  
Munetsugu Kaneko ◽  
Igor Men’shov ◽  
Yoshiaki Nakamura
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
Tube Wall ◽  
Reflected Shock Wave ◽  
Reflected Shock

scholarly journals An investigation of the interaction between a travelling shock wave and a solid rocket motor nozzle

2021 ◽  
Author(s):  
Harmanjit Singh Chopra
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
Reflected Shock Wave ◽  
Convergence Region ◽  
Rocket Motors ◽  
Additional Information ◽  
Reflected Shock ◽  
Solid Propellant Rocket ◽  
Computational Fluid Dynamics Cfd ◽  
Nozzle Geometries

A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle. A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour. A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle.A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour.Experimental and numerical pressure-time profiles confirm the appearance of transient radial wave activity following the initial incidence of the normal shock wave on the convergence region of the nozzle. The results establish that the strength of this activity is markedly dependent upon the nozzle convergence wall angle and the location within the shock tube

Non-equilibrium condensation of a vapour—gas mixture on a shock-tube endwall behind a reflected shock wave

1990 ◽  
Vol 6 (1) ◽  
pp. 25-42 ◽  
Author(s):  
Maerefat Mehdi ◽  
Shigeo Fujikawa ◽  
Teruaki Akamatsu
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
Reflected Shock Wave ◽  
Gas Mixture ◽  
Reflected Shock ◽  
Non Equilibrium

scholarly journals The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube

1973 ◽  
Vol 39 (328) ◽  
pp. 3699-3706 ◽  
Author(s):  
Tetsuo NISHIYAMA ◽  
Takuya KAGA
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Shock Tube ◽  
Reflected Shock Wave ◽  
Reflected Shock

scholarly journals An investigation of the interaction between a travelling shock wave and a solid rocket motor nozzle

2021 ◽  
Author(s):  
Harmanjit Singh Chopra
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
Reflected Shock Wave ◽  
Convergence Region ◽  
Rocket Motors ◽  
Additional Information ◽  
Reflected Shock ◽  
Solid Propellant Rocket ◽  
Computational Fluid Dynamics Cfd ◽  
Nozzle Geometries

A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle. A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour. A gasdynamic mechanism has been identified as a potential source of combustion instability in solid-propellant rocket motors (SRMs). This mechanism involves the reinforcement of a reflected shock wave in the nozzle convergence region of an SRM's exhaust nozzle.A shock tube apparatus was developed for the experimental component of this study. Various factors, such as the effect of different nozzle geometries and driven channel pressures, were examined. Also, a model of the shock tube was developed for computational fluid dynamics (CFD) simulations. These simulations were generated for comparison with the experimental results and to provide additional information regarding the nature of the flow behaviour.Experimental and numerical pressure-time profiles confirm the appearance of transient radial wave activity following the initial incidence of the normal shock wave on the convergence region of the nozzle. The results establish that the strength of this activity is markedly dependent upon the nozzle convergence wall angle and the location within the shock tube

scholarly journals The Interaction of a Reflected Shock Wave with the Contact Region in a Shock Tube

1975 ◽  
Vol 18 (121) ◽  
pp. 681-688 ◽  
Author(s):  
Kazuyasu MATSUO ◽  
Kazuyuki KAGE ◽  
Shigetoshi KAWAGOE
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
Contact Region ◽  
Reflected Shock Wave ◽  
Reflected Shock

scholarly journals The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube

1974 ◽  
Vol 17 (110) ◽  
pp. 1039-1046 ◽  
Author(s):  
Kazuyasu MATSUO ◽  
Shigetoshi KAWAGOE ◽  
Kazuyuki KAGE
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Shock Tube ◽  
Reflected Shock Wave ◽  
Reflected Shock

Development of Shock-Wave-Powered Actuators for High Speed Positioning

2011 ◽  
Vol 5 (6) ◽  
pp. 786-792 ◽  
Author(s):  
Akira Kotani ◽  
◽  
Toshiharu Tanaka ◽  
Atsushi Fujishiro ◽  
Keyword(s):  
Shock Wave ◽  
Shock Tube ◽  
High Speed ◽  
Initial Conditions ◽  
Reflected Shock Wave ◽  
Compressive Wave ◽  
Reflected Shock ◽  
Temperature And Pressure ◽  
Driver Section ◽  
End Wall

A shock wave is a compressive wave which propagates at supersonic speed. A shock wave is generated by the emission of energy for a very short duration by high speed phenomena, such as explosions, discharges, collisions, high speed flights, etc. Shock tube experiments have played an important role in the field of high speed gas dynamics. A shock tube is usually divided by a diaphragm into a driver section and a driven section. Generally, the initial conditions of the driver and driven sections are high and low pressure, respectively. When the diaphragm breaks, a shock wave is generated in the driven section. The density, temperature and pressure of the gas behind the shock wave rise discontinuously. The shock wave arrives at the end wall of the tube, and a reflected shock wave is generated by the reflection from the wall. The quantities behind the reflected shock wave rise further. If the shock wave can be generated continuously without the diaphragm needing to be changed, this phenomenon could possibly be applied to an actuator having a piston that moves at high speed. In this study, equipment powered by a shock wave is produced, and its performance is examined. The results show that piston movement generated by a shock wave is faster than that which is not and that the piston speeds depend on the initial conditions. Also, the characteristic of the actuator powered by the shock wave is revealed.

Sign in / Sign up

Export Citation Format

Share Document