A diagonal implicit scheme for computing flows with finite-rate chemistry

Eberhardt, Scott; Imlay, Scott T.

doi:10.2514/6.1990-1577

Cited by 37 publications

(19 citation statements)

References 7 publications

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“…The viscous fluxes are evaluated by central differencing. Time integration is performed with a CFL number of 0.1, which is combined with the diagonal point implicit method 24) for maintaining the stability of the source term.…”

Section: Numerical Methods and Conditionsmentioning

confidence: 99%

Numerical Analysis on the Nonequilibrium Phenomena of the Electronic Excitation Process behind Hypersonic Shock Waves

Yamada

Takayanagi

Suzuki

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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In this study, the nonequilibrium phenomena of the electronic excitation process behind hypersonic shock waves have been investigated through numerical analysis. In the analysis, the three-temperature model is employed and temperature profiles are computed along the distance from the shock front. In the three-temperature model, the translationalrotational, vibrational and electron-electronic excitation temperatures are separately described and the relaxation processes for each energy mode are considered. Numerical calculations are conducted under the conditions corresponding to the shock tube experiments conducted in our previous study and the results are compared with the experimental data. It is found that the calculated and measured vibrational temperature profiles are in good agreement. In contrast, the calculated electronic excitation temperature is much lower than the measured one, revealing the discrepancy in the modeling of the electronic excitation temperature. To investigate the effect of electron behavior, parametric studies are conducted using the three-temperature model. The calculated temperatures agree well with the measured temperatures by considering the electrons in the region ahead of the shock wave. This result suggests that the effect of electron behavior is significant for hypersonic shock waves and a detailed model to describe the nonequilibrium phenomena is needed.

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Section: Numerical Methods and Conditionsmentioning

confidence: 99%

Numerical Analysis on the Nonequilibrium Phenomena of the Electronic Excitation Process behind Hypersonic Shock Waves

Yamada

Takayanagi

Suzuki

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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“…Central difference was used for the viscous term. The point implicit method 8) was used for the source term of the chemical reaction. The MFGS method 9) was used for the time integral.…”

Section: )mentioning

confidence: 99%

Effect of the Location of an Incident Shock Wave on Combustion and Flow Field of Wall Fuel-Injection

Nakamura

Sato

Kobayashi

et al. 2008

Trans. Japan Soc. Aero. S Sci.

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Experimental and numerical studies on the interaction between combustion of a hydrogen jet and an incident shock wave were performed. When the incident shock wave was introduced upstream of the injection slot, the boundary-layer separation region was expanded extensively. The penetration height, defined as the height of the Mach disk, with the incident shock wave was less than that without the incident shock wave. Combustion was confirmed when the incident shock wave was introduced downstream of the fuel injection slot. However, combustion was not confirmed with the incident shock wave upstream of fuel injection slot. The mechanism of these phenomena was examined based on the numerical simulation results in terms of the characteristic residence time in the separation region near the fuel injection slot.

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“…The LU-SGS algorithm is applied to solve the implicit scheme. The diagonal implicit source term used by Eberhardt and Imlay [7] are employed. NS equations can be simply expressed as:…”

Section: Numerical Algorithm and Chemical Modelsmentioning

confidence: 99%

“…The detail definitions for above parameters refer to [6], [7]. The chemical reactions are introduced using 8 reactions in 7 species, chemistry kinetics model [8].…”

Section: Pu 332/99 Dq D(e-e N ) D(f-f)mentioning

confidence: 99%