The development of a variable Schmidt number model for jet-in-crossflows using genetic algorithms

Guo, Yanfei; He, Guoqing; Hsu, Andrew T.; Brankovic, A.; Syed, S. A.; Liu, N.-S.

doi:10.2514/6.1999-671

Cited by 7 publications

(4 citation statements)

References 7 publications

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“…In general the results for high Mach number, low wall temperature cases were improved over those utilizing the k-ε model alone. In 1999, another approach was taken by Guo et al to create a variable turbulent Schmidt number model [18]. In addition to the k-ε turbulence model, Guo modeled the turbulent species diffusion vector with a single transport equation.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Keistler

Xiao

Hassan

et al. 2006

36th AIAA Fluid Dynamics Conference and Exhibit

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Section: Introductionmentioning

confidence: 99%

Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Keistler

Xiao

Hassan

et al. 2006

36th AIAA Fluid Dynamics Conference and Exhibit

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“…Constant values for these coefficients are usually assumed in applications for low-and high-speed reacting flows of engineering interest, even though values for these coefficients have been shown to vary spatially. [35][36][37][38][39][40][41][42][43][44][45] Table 1. As one would expect, reducing the turbulent Schmidt number consistently intensified combustion due to enhanced species diffusion processes.…”

Section: Reynolds Heamass Flux Vectormentioning

confidence: 99%

Modeling of High Speed Reacting Flows: Established Practices and Future Challenges

Baurle

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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Computational fluid dynamics (CFD) has proven to be an invaluable tool for the design and analysis of highspeed propulsion devices. Massively parallel computing, together with the maturation of robust CFD codes, has made it possible to perform simulations of complete engine flowpaths. Steady-state Reynolds-Averaged Navier-Stokes simulations are now routinely used in the scramjet engine development cycle to determine optimal fuel injector arrangements, investigate trends noted during testing, and extract various measures of engine efficiency. Unfortunately, the turbulence and combustion models used in these codes have not changed significantly over the past decade. Hence, the CFD practitioner must often rely heavily on existing measurements (at similar flow conditions) to calibrate model coefficients on a caseby-case basis. This paper provides an overview of the modeled equations typically employed by commercialquality CFD codes for high-speed combustion applications. Careful attention is given to the approximations employed for each of the unclosed terms in the averaged equation set. The salient features (and shortcomings) of common models used to close these terms are covered in detail, and several academic efforts aimed at addressing these shortcomings are discussed.

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“…Constant values for these numbers are usually assumed in applications, although their values have been found to vary spatially. 9,10 Calculations performed by various authors 11,12,13 have shown strong sensitivity of the solution to these numbers, especially to Sct. Therefore, extreme care should be taken when attempting to characterize scramjet engines with constant turbulent transport coefficients.…”

Section: Vulcan Cfd Codementioning

confidence: 99%

Simulations of Cavity-stabilized Flames in Supersonic Flows Using Reduced Chemical Kinetic Mechanisms

Liu

Tam

et al. 2006

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The development of a variable Schmidt number model for jet-in-crossflows using genetic algorithms

Cited by 7 publications

References 7 publications

Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Modeling of High Speed Reacting Flows: Established Practices and Future Challenges

Simulations of Cavity-stabilized Flames in Supersonic Flows Using Reduced Chemical Kinetic Mechanisms

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