Mixing and Penetration Studies of Sonic Jets in a Mach 2 Freestream

Gruber, Mark; Nejadt, A. S.; Chen, T. H.; Dutton, J. C.

doi:10.2514/3.51427

Cited by 256 publications

(117 citation statements)

References 16 publications

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“…The results of this study demonstrated the limitation of the Boussinessq approximation of the two-equation RANS turbulence models in capturing the fundamental features of the vortically dominated flows. The hybrid RANS and LES method was used by Boles et al [43] to compare the flowfield results with those from the experiment of Gruber et al [44]. Despite the minor overprediction of the jet penetration into the crossflow, the results demonstrated good agreement with those from the experimental study.…”

supporting

confidence: 78%

Interaction of Vortex with Bow Shock Wave: Computational Model, Experimental Validation, Enhanced Mixing

2018

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A computational model is developed using a delayed detached-eddy simulation to examine the various aspects of shock-wave/vortex interactions, in which the specific case of naturally formed bow shock wave generated during a sonic injection into a supersonic crossflow is considered. The model is validated by comparing with experimental results obtained previously and is deployed to investigate the effects of shock/vortex interaction on mixing characteristics of supersonic flows. A vortex generator, in the form of a semispan wing section, is placed at an angle of attack upstream of an injection location. The resultant vortex interacts with the bow shock, and for a sufficiently strong interaction, there is breakdown of the supersonic vortex. The vortex bursting observed during the computational study is in a very good agreement with a previous physical model. The computational results demonstrate that the shock/vortex interaction can be an effective method of mixing enhancement because it results in redistribution and increase of vorticity in the flowfield, which enhances the entrainment and eventual mixing of injectant and supersonic crossflow.

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supporting

confidence: 78%

Interaction of Vortex with Bow Shock Wave: Computational Model, Experimental Validation, Enhanced Mixing

2018

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“…In contrast, the heightwise component behind the jet was higher than that around the outer jet boundary and mainstream. This high upward v region originated from the well-known longitudinal counter-rotating vortex pair (CVP) 13) formed in the transverse jet. The longitudinal CVP entrained the mainstream-air.…”

Section: Instantaneous Flow Structurementioning

confidence: 99%

Combined Stereo-PIV and PLIF Measurements of Transverse Injection in Mach 2 Supersonic Flow

Kouchi

Oka

Masuya

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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“…Understanding the physics of mixing in JISC is very important in order to get improvements in air-fuel mixing and successful combustion to achieve useful thrust from a scramjet engine. Gruber et al (1995) carried out an experimental study of transverse jet mixing. The free-stream conditions used in his experiment were Mach 2 and the jet entered into the free-stream at sonic velocity.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Rana

Thornber

Drikakis

2013

Engineering Applications of Computational Fluid Mechanics

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This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without chemical reaction/combustion in order to understand the fuel injection and air-fuel (hydrogen) mixing. The study is carried out in two parts; part one presents analysis of 2D HyShot-II geometry (without fuel injection) incorporating high temperature gas formulation which is validated against the NASA Thermally-Perfect-Gas code in order to obtain the combustion chamber inlet conditions. These combustor initial conditions are then utilized in part two for 3D combustion chamber simulations with hydrogen injection but cold flow where a digital filter based turbulent inflow boundary condition has been utilized. The purpose of the study is to understand the flow physics, hydrogen jet penetration and air & fuel mixing inside the HyShot-II combustor which is vital at the design stages. Various flow features are investigated such as the Mach number, velocity, pressure distributions, temperature, turbulent kinetic energy, Reynolds stresses and the effect of counter rotating vortices on mixing. The results of full geometry simulations are compared with computational results from the German Aerospace Centre, DLR, whereas due to unavailability of any data for hydrogen cold flow the validity of the results is based upon a similar validation case presented earlier (Rana et al., 2011b).

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Mixing and Penetration Studies of Sonic Jets in a Mach 2 Freestream

Cited by 256 publications

References 16 publications

Interaction of Vortex with Bow Shock Wave: Computational Model, Experimental Validation, Enhanced Mixing

Interaction of Vortex with Bow Shock Wave: Computational Model, Experimental Validation, Enhanced Mixing

Combined Stereo-PIV and PLIF Measurements of Transverse Injection in Mach 2 Supersonic Flow

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

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