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

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

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Interaction of Reflected Shock Wave with Shock Tube Wall

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ◽

10.2322/jjsass.52.153 ◽

2004 ◽

Vol 52 (603) ◽

pp. 153-159 ◽

Cited By ~ 3

Author(s):

Munetsugu Kaneko ◽

Igor Men’shov ◽

Yoshiaki Nakamura

Keyword(s):

Shock Wave ◽

Shock Tube ◽

Tube Wall ◽

Reflected Shock Wave ◽

Reflected Shock

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An experimental study of liquefaction shock waves

Journal of Fluid Mechanics ◽

10.1017/s0022112079001476 ◽

1979 ◽

Vol 95 (2) ◽

pp. 279-304 ◽

Cited By ~ 43

Author(s):

Georg Dettleff ◽

Philip A. Thompson ◽

Gerd E. A. Meier ◽

Hans-Dieter Speckmann

Keyword(s):

Shock Wave ◽

Incident Shock ◽

Shock Velocity ◽

Index Of Refraction ◽

Clear Liquid ◽

Two Phase ◽

Condensation Zone ◽

Temperature Index ◽

Reflected Shock ◽

Beam Attenuation

The existence of a liquefaction shock wave, a compression shock which converts vapour into liquid, has recently been predicted on physical grounds. The liquefaction shock was experimentally produced as the reflected shock at the closed end of a shock tube. Measurements of pressure, temperature, index of refraction and shock velocity confirm the existence of the shock and its general conformity to classical Rankine-Hugoniot conditions, with a discrepancy ∼ 10°C between measured and predicted liquid temperatures. Photographic observations confirmed the existence of a clear liquid phase and revealed the (unanticipated) presence of small two-phase torus-form rings. These rings are interpreted as vortices and are formed in or near the shockfront (∼ 50 rings/mm2 are visible near the shockfront at any given time). Separate experiments with the incident shock under conditions of partial liquefaction produced a fog behind the shock: measurements of laser-beam attenuation yielded the thickness of the condensation zone and estimates of the droplet size (∼ 10−7 m).

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

Journal of Fluid Mechanics ◽

10.1017/s0022112008005090 ◽

2009 ◽

Vol 622 ◽

pp. 33-62 ◽

Cited By ~ 101

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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