Improved k-ω-γ model for crossflow-induced transition prediction in hypersonic flow

Zhou, Lingjun; Li, Renfu; Hao, Zihui; Zaripov, Dinar; Yan, Chao

doi:10.1016/j.ijheatmasstransfer.2017.08.013

Cited by 31 publications

(2 citation statements)

References 41 publications

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“…It was extended to hypersonic transitional flows dominated by the first and second mode, and laminar separation in 2017 [17]. Wang and Fu [18] and Wang and Fu [19] also combined these models between 2009 and 2012 to design their k − ω − γ local model for hypersonic transitional flows, which was improved recently by Zhou et al ([20], [21], [22]).…”

Section: Nomenclaturementioning

confidence: 99%

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Chanteux

Bégou

Deniau

et al. 2022

AIAA AVIATION 2022 Forum

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Section: Nomenclaturementioning

confidence: 99%

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Chanteux

Bégou

Deniau

et al. 2022

AIAA AVIATION 2022 Forum

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“…When a turbulence model is used to analyze the flow field inside a scramjet intake, inaccurate boundary layer transition and SWBLI predictions could cause the results obtained to differ significantly from the actual flow behavior [40]. To overcome these limitations, research pertinent to the development and improvement of new and transition models [41][42][43] has attracted increased attention. The existing efforts to improve the model include the modification of the correlations of the γ-Re θt model [44][45][46] or both the equations and the correlations [47][48][49].…”

Section: Introductionmentioning

confidence: 99%

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$

Kang

Shin

Park

et al. 2021

International Journal of Aerospace Engineering

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The selection of an appropriate turbulence/transition model is critical when simulating the hypersonic flows based on the Reynolds-averaged Navier–Stokes (RANS) equation. In particular, a deep understanding of the validity, reliability, and limitations of existing models is an essential prerequisite to facilitate their further development. This paper reports on the assessment of two models dedicated to hypersonic boundary layer transition analysis. Both models are compared with two other models that are widely used in this field. The double ramp and shock wave laboratory scramjet intake cases are used for the validation and evaluation of the predictive performance of both models via comparison against experimental data. The results reveal that the appropriate selection of the transition model is critical to the attainment of accurate results. Moreover, the forebody of the scramjet combustion propulsion-01 (SCP-01) flight vehicle, which is a research model, is analyzed as a case study. The air intake performance of the SCP-01, as predicted by four models, is compared and analyzed at different flight altitude and Mach number conditions. The results reveal that the accuracy of the prediction of boundary layer and separated flow transitions significantly affects the flow field and corresponding air intake performance. Furthermore, the uncertainty of results obtained using the two models increases significantly with an increase in altitude. Finally, the reliability and limitations of the transition models considered in this study are examined.

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Computation of Hypersonic Transitional Flows Over Cones Using Gas-Kinetic Scheme Coupled with the Turbulence Model

Li¹,

Liu²,

Jiang³

et al. 2022

Lecture Notes in Electrical Engineering

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Improved k-ω-γ model for crossflow-induced transition prediction in hypersonic flow

Cited by 31 publications

References 41 publications

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$

Computation of Hypersonic Transitional Flows Over Cones Using Gas-Kinetic Scheme Coupled with the Turbulence Model

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Improved k-ω-γ model for crossflow-induced transition prediction in hypersonic flow

Cited by 31 publications

References 41 publications

Construction and Application of Transition Prediction Databased Method for 2nd Mode on Sharp Cone

Construction and Application of Transition Prediction Databased Method for 2nd Mode on Sharp Cone

Comparative Assessment of Modified γ - Re θ t

Computation of Hypersonic Transitional Flows Over Cones Using Gas-Kinetic Scheme Coupled with the Turbulence Model

Contact Info

Product

Resources

About

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$