Investigation of Hypersonic Intakes Using Reynolds Stress Modeling and Wavelet-Based Adaptation

Frauholz, Sarah; Bosco, Arianna; Reinartz, Birgit; Müller, Siegfried; Behr, Marek

doi:10.2514/1.j052966

Cited by 4 publications

(4 citation statements)

References 32 publications

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“…The computational grids are represented by block-structured parametric B-spline patches. All the key ingredients have been described in detail in the theses by Bramkamp [21], Lamby [22], and Müller [23], followed by numerous publications in which the solver has been extended and applied to a wide range of problems from subsonic to hypersonic flows, together with a thorough validation; for example, some recent publications are [24][25][26][27][28][29]. By now the QUADFLOW solver, as well as the underlying numerical methods, are well established.…”

Section: B Numerical Methodsmentioning

confidence: 99%

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

2016

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Edney type IV and type VII shock-shock interactions are complex hypersonic flow phenomena. They are characterized by a supersonic jet that reaches far into the flowfield. An experimental investigation of the inner jet structure is difficult, especially in cases where the jet is subject to high-frequency unsteady movements. The present paper provides insight into the jet structure and its movement by means of a highly resolved computational fluid dynamics analysis in thermochemical nonequilibrium that significantly exceeds the resolution of existing publications. Simulations of an Edney type IV interaction in nitrogen flow are presented. Advanced adaptation strategies allow for the identification and analysis of the mechanisms of the jet unsteadiness, resulting in a new classification of the unsteady flowfield behavior with respect to the periodic jet movement. This classification is based not only on wall quantities, but also on the core flowfield. The computations are supplemented by a grid sensitivity study. The second configuration is an Edney type VII interaction. This shock-shock interaction type was observed and defined in nitrogen flow by Yamamoto et al (Numerical Investigation of Shock/Vortex Interaction in Hypersonic Thermochemical Nonequilibrium Flow, Journal of Spacecraft and Rockets, Vol. 36, No. 2, 1999, pp. 240-246. The present results demonstrate that this interaction may also be observed in carbon-dioxide-dominated flow with a gas composition similar to the Martian atmosphere. The results provide insight into the jet structure of this less known interaction.

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Section: B Numerical Methodsmentioning

confidence: 99%

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

2016

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“…For load-balancing, we use the concept of space-filling curves [60]. Just recently this approach was successfully applied to hypersonic applications including fully three-dimensional computations of scramjet intakes [61].…”

Section: Numerical Methods a Quadflow Solvermentioning

confidence: 99%

“…The final adapted grid on level l = 4 has 3.5 million cells. Grid convergence was shown in [61] using a fixed transition point at the end of first ramp. The overall flow phenomena can be seen in Figure 11.…”

Section: A Swl Intakementioning

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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“…From their investigation, it also can be seen that on using SST kω model, the results obtained are very close to the available experimental values. Reynolds stress model for supersonic flow simulation was conducted by Frauholz et al [16], and they concluded that the model is capable of predicting boundary layer shockwave interaction effectively and effect of grid reduction is invariant of solution outcome. However, in the numerical simulation of strut scramjet engine, Reynolds Stress model has not yet been used.…”

Section: Introductionmentioning

confidence: 99%

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

Debnath¹,

Tjprc²

2019

IJMPERD

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In recent years, many researchers have used numerical simulation to investigate scramjet engine because, setting up of testing facilities for scramjet engine is very expensive. Completion of simulation work in less time is costeffective but, it is also important to achieve good outcome from the simulation work. In this context, the use of appropriate turbulent model for the simulation for DLR scramjet engine is a vital aspect. From the available literature, it is seen that many researchers have used Reynolds stress, SST kω and RNG k-ε models in the field of supersonic flow and combustion. Thus, in this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Finally, from the study, it is found that using SST kω model for numerical simulation of DLR scramjet engine results in more accuracy at a lesser computational time.Impact Factor (JCC): 7.6197 SCOPUS Indexed Journal NAAS Rating: 3.11The simulation in this study is conducted on a workstation equipped with Intel Xenon processor of 8 GB memory.The computational time spend for cold flow simulation using RNG k-ε and SST k-ω models were approximately 16 hours and that for using Reynolds Stress model was 31 hours. Whereas, the computational time spends for reactive flow simulation using RNG k-ε and SST k-ω models were approximately 36.5 hours and that for using Reynolds Stress model was approximately 74 hours. CONCLUSIONSIn this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Base on the results found from the simulations, the following conclusions are drawn.• The results predicted by SSTk-ω model is found to be more accurate than the results predicted by RNG k-ε and Reynolds Stress models in comparison with experimental results.• In reference to the results obtained by using SSTk-ω model, it is seen that the average deviation in mixing and combustion efficiency predicted by RNG k-ε model is less compared with Reynolds Stress model.• The computational time required for simulations using RNG k-ε and SST k-ω models are substantially less in comparison with Reynolds Stress model.• Thus, from this study, it can be finally establish that the use of SST kω model for numerical simulation of DLR scramjet engine will provide more accurate result at a lesser computational time.

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Investigation of Hypersonic Intakes Using Reynolds Stress Modeling and Wavelet-Based Adaptation

Cited by 4 publications

References 32 publications

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

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

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

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