3D numerical simulation of the supersonic combustion of H<sub>2</sub>

Dinde, Prashant; Rajasekaran, A.; Babu, V.

doi:10.1017/s0001924000001640

Cited by 8 publications

(4 citation statements)

References 12 publications

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“…The hydrogen injection conditions are adjusted so as to obtain a sonic injection with a mass flow rate to maintain the equivalence ratio of 0.0125 [87]. The temperature and pressure are high enough to produce auto-ignition of the hydrogen-air mixture.…”

Section: Physical Modelmentioning

confidence: 99%

“…The grid packing near the wall region is used to resolve the turbulent boundary layer for the wall function formulation. Also, the grid packing scheme is used in the wake region to resolve the mixing and diffusion effects of hydrogen effectively [87]. Density based on second order finite volume discretization method using explicit solver has been employed.…”

Section: Numerical Simulation and Boundary Conditionsmentioning

confidence: 99%

“…Near wall mesh has been chosen so that wall y + values are less than 100. This is an acceptable value for turbulent calculations with standard wall functions [87]. The complete flow domain within the combustor has been initialized using the prescribed inlet conditions from experimental data.…”

Section: Numerical Simulation and Boundary Conditionsmentioning

confidence: 99%

See 2 more Smart Citations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Section: Physical Modelmentioning

confidence: 99%

Section: Numerical Simulation and Boundary Conditionsmentioning

confidence: 99%

See 1 more Smart Citation

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…However, in recent years, many researchers have used other computational models to investigate scramjet engine. Dinde et al [12] have numerically investigated scramjet combustor by introducing RNG k-ε turbulence model with finite rate single step chemistry model.…”

Section: Introductionmentioning

confidence: 99%

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

Debnath¹,

Tjprc²

2019

IJMPERD

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In recent years, many researchers have used numerical simulation to investigate scramjet engine because, setting up of testing facilities for scramjet engine is very expensive. Completion of simulation work in less time is costeffective but, it is also important to achieve good outcome from the simulation work. In this context, the use of appropriate turbulent model for the simulation for DLR scramjet engine is a vital aspect. From the available literature, it is seen that many researchers have used Reynolds stress, SST kω and RNG k-ε models in the field of supersonic flow and combustion. Thus, in this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Finally, from the study, it is found that using SST kω model for numerical simulation of DLR scramjet engine results in more accuracy at a lesser computational time.Impact Factor (JCC): 7.6197 SCOPUS Indexed Journal NAAS Rating: 3.11The simulation in this study is conducted on a workstation equipped with Intel Xenon processor of 8 GB memory.The computational time spend for cold flow simulation using RNG k-ε and SST k-ω models were approximately 16 hours and that for using Reynolds Stress model was 31 hours. Whereas, the computational time spends for reactive flow simulation using RNG k-ε and SST k-ω models were approximately 36.5 hours and that for using Reynolds Stress model was approximately 74 hours. CONCLUSIONSIn this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Base on the results found from the simulations, the following conclusions are drawn.• The results predicted by SSTk-ω model is found to be more accurate than the results predicted by RNG k-ε and Reynolds Stress models in comparison with experimental results.• In reference to the results obtained by using SSTk-ω model, it is seen that the average deviation in mixing and combustion efficiency predicted by RNG k-ε model is less compared with Reynolds Stress model.• The computational time required for simulations using RNG k-ε and SST k-ω models are substantially less in comparison with Reynolds Stress model.• Thus, from this study, it can be finally establish that the use of SST kω model for numerical simulation of DLR scramjet engine will provide more accurate result at a lesser computational time.

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Investigation on the effect of strut configurations and locations on the combustion performance of a typical scramjet combustor

Huang

2015

J Mech Sci Technol

112

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3D numerical simulation of the supersonic combustion of H₂

Cited by 8 publications

References 12 publications

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

Investigation on the effect of strut configurations and locations on the combustion performance of a typical scramjet combustor

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3D numerical simulation of the supersonic combustion of H2

Cited by 8 publications

References 12 publications

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

Investigation on the effect of strut configurations and locations on the combustion performance of a typical scramjet combustor

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3D numerical simulation of the supersonic combustion of H₂