Radiative Transfer Effects on the Flow Field and Heat Transfer behind a Reflected Shock Wave in Air

1967 ◽  
Vol 10 (8) ◽  
pp. 1785 ◽  
Author(s):  
John D. Anderson
Keyword(s):  
Heat Transfer ◽  
Shock Wave ◽  
Radiative Transfer ◽  
Flow Field ◽  
Reflected Shock Wave ◽  
Transfer Effects ◽  
Reflected Shock

Explosion near the ground: a solution to the multi-shock problem in cylindrical symmetry by the particle trajectory method

1977 ◽  
Vol 358 (1692) ◽  
pp. 31-46 ◽  
Keyword(s):  
Shock Wave ◽  
Shock Waves ◽  
Flow Field ◽  
Ground Surface ◽  
Cylindrical Symmetry ◽  
Theoretical Development ◽  
Reflected Shock Wave ◽  
Particle Trajectories ◽  
Reflected Shock ◽  
Cylindrically Symmetric

A theoretical development is described whereby cylindrically symmetric flows involving multiple shock waves may be mapped in both time and space. The theory is an extension of earlier work by Dewey which was restricted to flows with spherical symmetry and in which only one shock wave was present. The method requires a knowledge of the trajectories of individual air elements from which the density can be calculated by using the Lagrangian form of the equation of continuity. The other thermodynamic variables can be derived by assuming that, except in the shock waves, the flow is reversible and adiabatic. The theory has been applied to an investigation of the flow field associated with the explosion of 479 kg of TNT placed 22 m above the ground surface. The flow field is spherically symmetric until the initial shock wave is reflected from the ground after which it is symmetrical in azimuth but not in elevation. The presence of the reflected shock wave introduces a second shock wave into the problem which must be included in the analysis in order to obtain a complete description of the flow. The particle trajectories were obtained by using an array of smoke puffs whose motions were followed photographically. The results obtained by analysing the particle trajectories by the theoretical approach described in this paper have been compared with the results obtained from piezo-electric pressure transducers at several points in the flow field and strikingly good correlation has been noted. A brief discussion is included on the effects of certain simplifications introduced into the analysis for reasons of practical convenience. It has been concluded that the theory proposed is a valid one having general application to situations where gasdynamic effects are preponderant.

Heat transfer behind a reflected shock wave in a two-phase gas-dynamic flow

1975 ◽  
Vol 8 (2) ◽  
pp. 282-289
Author(s):  
A. A. Kon'kov ◽  
G. N. Nikolaev ◽  
Yu. A. Polyakov
Keyword(s):  
Heat Transfer ◽  
Shock Wave ◽  
Reflected Shock Wave ◽  
Dynamic Flow ◽  
Two Phase ◽  
Reflected Shock ◽  
Gas Dynamic

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 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

Three-dimensional instantaneous structure of a shock wave/turbulent boundary layer interaction

2009 ◽  
Vol 622 ◽  
pp. 33-62 ◽  
Author(s):  
R. A. HUMBLE ◽  
G. E. ELSINGA ◽  
F. SCARANO ◽  
B. W. van OUDHEUSDEN
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulent Boundary Layer ◽  
High Speed ◽  
Large Scale ◽  
Three Dimensional ◽  
Reflected Shock Wave ◽  
Layer Interaction ◽  
Reflected Shock ◽  
Boundary Layer Interaction

An experimental study is carried out to investigate the three-dimensional instantaneous structure of an incident shock wave/turbulent boundary layer interaction at Mach 2.1 using tomographic particle image velocimetry. Large-scale coherent motions within the incoming boundary layer are observed, in the form of three-dimensional streamwise-elongated regions of relatively low- and high-speed fluid, similar to what has been reported in other supersonic boundary layers. Three-dimensional vortical structures are found to be associated with the low-speed regions, in a way that can be explained by the hairpin packet model. The instantaneous reflected shock wave pattern is observed to conform to the low- and high-speed regions as they enter the interaction, and its organization may be qualitatively decomposed into streamwise translation and spanwise rippling patterns, in agreement with what has been observed in direct numerical simulations. The results are used to construct a conceptual model of the three-dimensional unsteady flow organization of the interaction.

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