Application of Crossflow Transition Criteria to Local Correlation-Based Transition Model

Watanabe, Yuto; Misaka, Takashi; Obayashi, Shigeru; Arima, Toshiyuki; Yamaguchi, Yoshihiro

doi:10.2514/6.2009-1145

Cited by 15 publications

(2 citation statements)

References 11 publications

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“…A first attempt to introduce crossflow transition into the γ-Re θ model was done by incorporating a parameter similar to the Görtler number [92] assuming an analogy between Görtler and crossflow instabilities [93]. A different approach using ONERA's 1 C1 criterion [61] for crossflow transition and the Falkner-Skan and Cooke (FSC) equations [94][95] was published in [96][97].…”

Section: Crossflow Transition In Transport Equation Approachesmentioning

confidence: 99%

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

Krumbein

Krimmelbein

Grabe

et al. 2015

45th AIAA Fluid Dynamics Conference

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Section: Crossflow Transition In Transport Equation Approachesmentioning

confidence: 99%

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

Krumbein

Krimmelbein

Grabe

et al. 2015

45th AIAA Fluid Dynamics Conference

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“…Grabe/Krumbein [36] implemented the transition model combined with the SST model within the DLR TAU code and introduced a modification for cross-flow transition. Watanabe also modified the transition model for crossflow transition [37]. In addition, You [38] proposed a new equation for the effective intermittency for hypersonic flows taking the pressure gradient via the acceleration parameter λ θ into account.…”

mentioning

confidence: 99%

Transition Prediction for Scramjets Using γ-Reθt Model Coupled to Two Turbulence Models

Frauholz

Reinartz

Müller

et al. 2015

Journal of Propulsion and Power

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Because of viscous interaction in hypersonic flows, the state of the boundary layer significantly influences possible shock-wave boundary-layer interaction as well as surface heat loads. Hence, for engineering applications, the efficient numerical prediction of the laminar-to-turbulent transition is a challenging and important task. Within the framework of the Reynolds-averaged Navier-Stokes equations, Langtry-Menter proposed the γ-Re θ t transition model using two transport equations for the intermittency and Re θ t combined with the shear stress transport turbulence model. The transition model contains two empirical correlations for the onset and length of transition. Langtry-Menter designed and validated the correlations for the subsonic and transonic flow regimes. For applications in the hypersonic flow regime, the development of a new set of correlations proved necessary. Within this paper, we propose a next step and couple the transition model with the Speziale-Sarkar-Gatski/Launder-Reece-Rodi ω Reynolds stress turbulence model, which we found to be well suited for scramjet intake simulations. First, we illustrate the necessary modifications of the Reynolds stress model and the hypersonic in-house correlations using a hypersonic flat plate test case. Next, the transition model is successfully validated for its use coupled to both turbulence models using a hypersonic double ramp test case. Regardless of the turbulence model, the transition model is able to correctly predict the transition process compared to experimental data. In addition, we apply the transition model combined with both turbulence models to three different fully three-dimensional scramjet intake configurations that are experimentally investigated in wind tunnel facilities. The agreement with the available experimental data is also shown. Nomenclature c p = specific heat at constant pressure, pressure coefficient, -D ij = diffusion tensor for Reynolds stresses, m 2 ∕s 3 E = specific total energy, m 2 ∕s 2 E γ = destruction term of γ transport equation, m∕s F length = transition length function, empirical correlation, -H = total specific enthalpy, m 2 ∕s 2 I = turbulent intensity,k = turbulent kinetic energy, m 2 ∕s 2 L = maximum refinement level,l = local refinement level, -M = Mach number, -M ij = turbulent mass flux tensor for Reynolds stresses, m 2 ∕s 3 P ij = production tensor for Reynolds stresses, m 2 ∕s 3 P γ = production term of γ transport equation, m∕s P θ t = production term of Re θt transport equation, m∕s p = pressure, Pa p t = total pressure, Pa q i = component of heat flux vector, W∕m 2 q t k = turbulent heat flux, W∕m 2 Re = Reynolds number, 1∕m Re θt = transition onset Reynolds number, -Re θ c = critical Reynolds number, empirical correlation, -Res drop = averaged density residual, at which adaptations are performed, -R ij = Reynolds stress tensor, m 2 ∕s 2 St = Stanton number, -T = temperature, K T w = wall temperature, K T 0 = total temperature, K t = time, s u i = velocity component, m∕s x i = Cartesian coordinates compon...

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An Algebraic LCTM Model for Laminar–Turbulent Transition Prediction

Menter

Matyushenko

Lechner

et al. 2022

Flow Turbulence Combust

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Application of Crossflow Transition Criteria to Local Correlation-Based Transition Model

Cited by 15 publications

References 11 publications

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

Transition Prediction for Scramjets Using γ-Reθt Model Coupled to Two Turbulence Models

An Algebraic LCTM Model for Laminar–Turbulent Transition Prediction

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