Improved γ-Re model for heat transfer prediction of hypersonic boundary layer transition

Hao, Zihui; Yan, Chao; Qin, Yupei; Zhou, Lingjun

doi:10.1016/j.ijheatmasstransfer.2016.11.052

Cited by 23 publications

(8 citation statements)

References 16 publications

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“…The calculated boundary layer at that position is in a full turbulent state, which is ahead of the completion of the transition at 0.90L . In contrast, the value of 12 H as predicted by using the improved model drops to 1.5 near the point 0.90L , which is in good agreement with the experimental measurement. The intermittency factor  is an important parameter to characterize the flow.…”

Section: Test Case 2: Naca 66(mod)-312 Hydrofoilsupporting

confidence: 83%

“…Figure 16 shows the boundary layer shape factor distribution. It is shown that 12 H predicted by using the original model is close to the experimental value in the leading edge region of the hydrofoil, but sharply deviates from the experimental value at = 0.79…”

Section: Test Case 2: Naca 66(mod)-312 Hydrofoilmentioning

confidence: 69%

“…Xia and Chen [11] simplified the SSTt Re   transition model by omitting the t Re  transport equation to establish a new empirical relation between the length parameter of the transition area and the critical momentum thickness Reynolds number. Hao et al [12] put the Reynolds number and the Mach number into the empirical relations to consider the compressibility of the hypersonic flow. Choi and Kwon [13] developed empirical relations by taking the crossflow boundary layer transition into consideration, to yield a relationship for flows with strong three-dimensionality.…”

Section: Introduction mentioning

confidence: 99%

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Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

Wang

et al. 2021

J Hydrodyn

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Section: Test Case 2: Naca 66(mod)-312 Hydrofoilsupporting

confidence: 83%

Section: Test Case 2: Naca 66(mod)-312 Hydrofoilmentioning

confidence: 69%

Section: Introduction mentioning

confidence: 99%

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Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

Wang

et al. 2021

J Hydrodyn

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“…The original

\gamma

‐

R{e}_{\theta }

transition model was developed for incompressible flows, 37 and Hao et al 38 extended it to compressible flows, which is the form used in this article.

\gamma

‐

R{e}_{\theta }

transition model is based on the k ‐

\omega

SST turbulence model by introducing the intermittency factor

\gamma

and the local transition onset momentum‐thickness Reynolds number

\tilde{R{e}_{\theta t}}

, whose transport equations are

({, \begin{cases} \frac{\partial (ρ γ)}{\partial t} + \frac{\partial ((), ρ U_{j} γ)}{\partial x_{j}} = P_{γ} prefix- D_{γ} + \frac{\partial}{\partial x_{j}} ([], ((), μ + \frac{μ_{t}}{σ_{γ}}) \frac{\partial γ}{\partial x_{j}}), \\ \frac{\partial ((), ρ \overset{R e_{θ t}}{true})}{\partial t} + \frac{\partial ((), ρ U_{j} \overset{R e_{θ t}}{true})}{\partial x_{j}} = P_{θ t} + \frac{\partial}{\partial x_{j}} ([], σ_{θ t} ((), μ + μ_{<...})) \end{cases})

…”

Section: Numerical Results and Discussion Of The Correction Methodsmentioning

confidence: 99%

A correction for Reynolds‐averaged‐Navier–Stokes turbulence model under the effect of shock waves in hypersonic flows

Tian

Gao

Lee

2022

Numerical Methods in Fluids

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Studies on the unphysical increase of turbulent quantities for RANS simulation induced by shock waves in hypersonic flows are carried out. Numerical experiments on the hypersonic flow over a blunt body reveal that the phenomenon of unphysical increase of turbulent quantities across the detached shock wave is induced by the strain-rate-based production terms of the k-𝜔 and k-𝜔 SST turbulence models, which leads to the over-prediction of aerothermal prediction.While this phenomenon does not occur for Spalart-Allmaras (S-A) turbulence model because of its vorticity-based production term. In order to eliminate this unphysical phenomenon, and to maintain the accuracy of the original models for boundary layer and separation flows, a new correction method for the k-𝜔 and k-𝜔 SST models is proposed: by comparing the orders of magnitude between the strain-rate-based and vorticity-based production terms, the vorticity-based production term is used near the shock waves, while the original strain-rate-based production term is still used in other regions. Finally, the correction method is applied to turbulence and transition flows over blunt bodies, and the numerical results show that the correction method effectively eliminates the unphysical increase of turbulent quantities across shock waves and improves the accuracy of aerothermal and transition onset location prediction.

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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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Improved γ-Re model for heat transfer prediction of hypersonic boundary layer transition

Cited by 23 publications

References 16 publications

Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

A correction for Reynolds‐averaged‐Navier–Stokes turbulence model under the effect of shock waves in hypersonic flows

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

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Improved γ-Re model for heat transfer prediction of hypersonic boundary layer transition

Cited by 23 publications

References 16 publications

Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

Improvement of the SST γ-Reθt transition model for flows along a curved hydrofoil

A correction for Reynolds‐averaged‐Navier–Stokes turbulence model under the effect of shock waves in hypersonic flows

Comparative Assessment of Modified γ - Re θ t

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