Progress Toward Shock Enhancement of Supersonic Combustion Processes

Marble, Frank E.; Hendricks, G. J.; Zukoski, E. E.

doi:10.1007/978-1-4613-9631-4_43

Cited by 51 publications

(46 citation statements)

References 14 publications

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“…Marble, Hendricks and Zukoski 4 suggested the above as a canonical model for the case of the passage of a cylindrical jet of hydrogen fuel through an oblique shock wave. As the column of light gas passes through the pressure gradient associated with a weak oblique shock, stream wise vorticity will be deposited on the fuel air interface.…”

Section: Shock-enhanced Mixingmentioning

confidence: 99%

Investigation of a contoured wall injector for hypervelocity mixing augmentation

1993

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Section: Shock-enhanced Mixingmentioning

confidence: 99%

Investigation of a contoured wall injector for hypervelocity mixing augmentation

1993

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“…When the very exacting requirement for very rapid mixing and combustion of hydrogen and air in the Supersonic Combustion Ramjet (SCRAMJET) became clear, we pro ceded to investigate, Marble, Hendricks and Zukoski (1987), the details of the mixing process induced by shock interaction with a jet of hydrogen in air.…”

Section: Introductionmentioning

confidence: 99%

Shock enhancement and control of hypersonic mixing and combustion

Marble

Zukoski

Jacobs

et al. 1990

26th Joint Propulsion Conference

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The possibility that shock enhanced mixing can substantially increase the rate of mixing between coflowing streams of hydrogen and air has been studied in experimental and computational investigations. Early numerical computations indicated that the steady interaction between a weak shock in air with a coflowing hydrogen jet can be well approximated by the two-dimensional time-dependent interaction between a weak shock and an initially circular region filled with hydrogen imbedded in air. An experimental investigation of the latter process has been carned out in the Caltech 17 Inch Shock Tube in experiments in which the laser induced fluorescence of byacetyl dye is used as a tracer for the motion of the helium gas after shock waves have passed across the helium cylinder. The flow field has also been studied using an Euler code computation of the flow field. Both investigations show that the shock impinging process causes the light gas cylinder to split into two parts. One of these mixes rapidly with air and the other forms a stably stratified vortex pair which mixes more slowly; about 60% of the light gas mixes rapidly with the ambient fluid. The geometry of the flow field and the mixing process and scaling parameters are discussed here. The success of this program encouraged the exploration of a low drag injection system in which the basic concept of shock generated streamwise vorticity could be incorporated in an injector for a Scramjet combustor at Mach numbers between 5 and 8. The results of a substantial computational program and a description of the wind tunnel model

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“…Meshkov [13]. It is of importance to applications ranging from astrophysics [14], inertial confinement fusion [15] to supersonic combustion [16,17]. The fluid configuration leading to a frequently considered RMI problem is shown in Fig.…”

Section: Shock Acceleration Of a Gas Cylindermentioning

confidence: 99%

Prediction of Chemical Laser Flow

Vorobieff¹,

Truman²

2006

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Executive summaryThe scope of the work as proposed to the funding agency was to carry out numerical calculations of high-speed mixing flows using GASP, a computational fluid dynamics (CFD) code. The ultimate goal is to use GASP for prediction and optimization of chemical laser flows. To do it, one must have confidence in the performance of the hydrodynamic and mixing part of the code.For complex numerical simulations, it is essential to perform code validation -a quantitative comparison of numerical results with experimental results confirming that the code faithfully reproduces the physics of the real problem. Two detailed validation exercises were performed with GASP:" Simulation of a shock-accelerated mixing flow. This validation exercise compared the numerical results produced by GASP with highly-resolved experimental data on flows subject to Richtmyer-Meshkov instability (RMI), the preferred test problem for quantitative assessment of the performance of CFD codes in prediction of the properties of high-speed mixing flows. The validation problem revealed that GASP can faithfully reproduce all the large-scale quantitative properties of the flow. We also gained important additional insights into the strengths and limitations of GASP (and other numerical codes) in prediction of disordered small scales in flows transitioning to turbulence." General jet-in-crossflow problem. The problem of a supersonic jet discharging into a supersonic crossflow presents a significant computational challenge, yet provides a valuable validation exercise when the results are compared with experimental data. The conditions for this exercise were chosen to achieve two goals: -Provide comparison with best experimental data available in open literature.-Test the code in a generic configuration that can be easily modified to represent a specific chemical laser nozzle injection scheme.The agreement with the experimental data was quite good, yet subtle features of the flow that were not apparent in the experiment were revealed by the simulation.The results of our work are as follows."* We found the hydrodynamic model used in GASP to be suitable for prediction of mixing in chemical laser flows."* We found the error in prediction of the geometry of large-scale features (e.g., counter-rotating vortex pairs) not to exceed 10-15% when compared with experiment.

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Progress Toward Shock Enhancement of Supersonic Combustion Processes

Cited by 51 publications

References 14 publications

Investigation of a contoured wall injector for hypervelocity mixing augmentation

Investigation of a contoured wall injector for hypervelocity mixing augmentation

Shock enhancement and control of hypersonic mixing and combustion

Prediction of Chemical Laser Flow

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