Compressibility Correction to k−ω Models for Hypersonic Turbulent Boundary Layers

Danis, Mustafa E.; Durbin, Paul A.

doi:10.2514/1.j062027

Cited by 10 publications

(2 citation statements)

References 19 publications

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“…To overcome these problems especially in the hypersonic regime, recent studies proposed compressibility corrections (McDaniel et al. 2016; Nichols 2019; Danis & Durbin 2022; Hendrickson, Subbareddy & Candler 2022) reporting significant improvements. The non-eddy-resolving nature of RANS makes their adoption in highly unsteady flows such as shock-boundary layer interaction problems also challenging (Wadhams, Holden & Maclean 2014).…”

Section: Introductionsupporting

confidence: 70%

“…Reynolds-averaged Navier-Stokes calculations are preferred in engineering design, in spite of their poor accuracy at hypersonic conditions (Wilcox 2006) and sensitivity to model parameters (Roys & Blottner 2006). To overcome these problems especially in the hypersonic regime, recent studies proposed compressibility corrections (McDaniel et al 2016;Nichols 2019;Danis & Durbin 2022;Hendrickson, Subbareddy & Candler 2022) reporting significant improvements. The non-eddy-resolving nature of RANS makes their adoption in highly unsteady flows such as shock-boundary layer interaction problems also challenging (Wadhams, Holden & Maclean 2014).…”

Section: Motivationmentioning

confidence: 99%

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Sub-filter-scale shear stress analysis in hypersonic turbulent Couette flow

Toki,

Sousa,

Chen

et al. 2024

J. Fluid Mech.

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Direct numerical simulations of hypersonic turbulent Couette flows are performed for top-wall Mach numbers of 6, 7 and 8, inspired by non-reactive high-enthalpy wind tunnel free-stream conditions, with the goal of analysing the physical processes driving the sub-filter-scale (SFS) stresses to inform development of large-eddy simulation techniques for hypersonic wall-bounded flows. Semi-local scaling laws collapse mean profiles and second-order turbulent statistics well, in spite of the strong wall-normal gradients of temperature and density. On the other hand, the SFS shear stresses exhibit an unexpected profile characterized by a region of pronounced shear stress deficit, which becomes more pronounced for higher Mach numbers. Instantaneous visualizations suggest that the SFS shear stress deficit is induced by the counter-gradient resolved momentum transport driven by residual velocity motions at the interface between high-density low-speed streaks being ejected away from the wall, and low-density high-speed ones replacing the displaced fluid, qualifying this as a compressibility effect. It is shown that the SFS shear stresses are primarily driven by second-order interactions between residual velocities, in spite of their triply nonlinear nature. This, in turn, motivated a statistical quadrant analysis revealing the presence of a SFS shear stress deficit, that is, SFS processes driving momentum transport of the resolved field towards the top wall. Additionally, higher-Reynolds-number simulations reveal that there is an upper limit of spatial filter widths to resolve large-scale structures, and such deficit is observable at any Reynolds number when a reasonable spatial filter is applied.

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Section: Introductionsupporting

confidence: 70%

Section: Motivationmentioning

confidence: 99%

Sub-filter-scale shear stress analysis in hypersonic turbulent Couette flow

Toki,

Sousa,

Chen

et al. 2024

J. Fluid Mech.

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A new non‐equilibrium modification of the k−ω$$ k-\omega $$ turbulence model for supersonic turbulent flows with transverse jet

Naimanova,

Beketaeva

2024

Numerical Methods in Fluids

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The goal of this research is to propose a new modification of a non‐equilibrium effect in the turbulence model to better predict high‐speed turbulent flows. For that, the two local compressibility coefficients are included in the balance production/dissipation terms in a specific dissipation rate equation. The specific dissipation rate reacts to changes in the local Mach number and density through these local coefficients. The developed model is applied to the numerical simulation of the spatial supersonic turbulent airflow with round hydrogen injection. In that, the effects of the proposed turbulence model on the flow field behavior (shock wave and vortex formations, shock wave/boundary layer interaction, and mixture layer) are studied via the solution of three‐dimensional Favre‐averaged Navier–Stokes equations with a third‐order Essentially Non‐Oscillatory scheme. A series of numerical experiments are performed, in which an allowable range of local constants by comparing results with experimental data is obtained. The non‐equilibrium modification by simultaneous decrease of the turbulence kinetic energy and increase of the specific dissipation rate gives a good agreement of the hydrogen depth penetration with experimental data. Also, the numerical experiment of the supersonic airflow with a nitrogen jet shows wall pressure distribution is consistent well with experimental data.

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