Effect of Suction Gap and Central Strut on the Interior Scramjet Intake Flow

Reinartz, Birgit; Remer, Michał; Gaisbauer, U.

doi:10.2514/6.2012-5941

Cited by 3 publications

(3 citation statements)

References 7 publications

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“…Figure 20 (left) shows the final level l = 4 grid. Information about previous numerical studies can be found in [17,70].…”

Section: Million Cellsmentioning

confidence: 99%

“…A common engineering approach to model transition is the use of fixed transition points [15,16], which is computationally cheap and easy to implement. However, often the transition point is not known a priori, e.g., from experiments [17]. Hence, advanced methods that resolve the transition process are necessary.…”

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confidence: 99%

“…left) shows the final level l = 4 grid. Information about previous numerical studies can be found in[17,70].The computation of the RSM-Tr model is used to visualize the general flow features in Figure20(right). The incoming flow is compressed and decelerated by the strong ramp shock wave and by the weaker side wall shock wave.…”

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confidence: 99%

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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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“…Figure 20 (left) shows the final level l = 4 grid. Information about previous numerical studies can be found in [17,70].…”

Section: Million Cellsmentioning

confidence: 99%

mentioning

confidence: 99%