Comparison of the predictive capabilities of several turbulence models

Rumsey, Christopher L.; Vatsa, Veer N.

doi:10.2514/3.46749

Cited by 25 publications

(13 citation statements)

References 11 publications

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“…The comparison of several turbulence models has been done by many groups [4,5]. For two-dimensional airfoil, several turbulence models are tested and analyzed by Douvi C.Eleni [6] and the validation is based on very detailed wind tunnel data.…”

Section: Operating Conditions and Model Of Turbulencementioning

confidence: 99%

The Study on Longitudinal Aerodynamic Characteristics of a Novel MAV Layout

Wei

Song

Wang

2015

Procedia Engineering

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In this paper, a study concerning the longitudinal aerodynamics of a Micro Air Vehicle (MAV) with novel layout is presented using both numerical simulations and experimental techniques. Numerical simulations are performed under the identical conditions of low Reynolds number about 10 6 and low aspect ratio about 2.5 and comparisons are made with the experimental wind tunnel measurements to verify the validity. Overall, experimental and numerical data match well for lift and pitching moment before the stall angle, and the same trend is presented for drag. Additional study of wing-tip flow and included angle flow between two semi-wings are illustrated in some sections. The lower semi-wing has much effect on the upper one in many aerodynamic performances. Compared with the typical MAVs, it has lower wing loading, higher payload, and better stability, so it is suitable to be multitasking MAV.

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Section: Operating Conditions and Model Of Turbulencementioning

confidence: 99%

The Study on Longitudinal Aerodynamic Characteristics of a Novel MAV Layout

Wei

Song

Wang

2015

Procedia Engineering

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“…Figure 3 shows the Q isosurfaces [38] of the turbulent flowfield. Although the grid 80 3 is not sufficiently refined to provide a realistic description of the flow structures, one can see however the existence of vortical structures called fine-scale worms. This figure can be qualitatively compared with Figure 3 of Reference [36] which is of better resolution 128 3 , showing the isovorticity surfaces.…”

Section: Decay Of Isotropic Spectrummentioning

confidence: 99%

“…Although the grid 80 3 is not sufficiently refined to provide a realistic description of the flow structures, one can see however the existence of vortical structures called fine-scale worms. This figure can be qualitatively compared with Figure 3 of Reference [36] which is of better resolution 128 3 , showing the isovorticity surfaces. Figures 4 and 5 display the decay of the three-dimensional spectra starting from the initial time, corresponding to different values of the coefficient and different RungeKutta schemes.…”

Section: Decay Of Isotropic Spectrummentioning

confidence: 99%

“…As it will be shown in the following, the vector of the mean variables U m =¯ [1,ũ 1 ,ũ 2 ,ũ 3 , E] T can be computed by a centered scheme in space discritization if associated with a fourth-order Runge-Kutta scheme in time or by a weighted scheme of more or less centered formulation, where 1 but not equal to zero if associated with a lower time accurate scheme for suppressing the spurious oscillations and discontinuities produced by a purely space centered scheme. On the contrary, the vector of the turbulent variables U t =¯ [ ( 11 ) is computed by a more or less upwind scheme obtained for = 1, depending on the slope limiters that are activated in the presence of discontinuities.…”

Section: Space Discretizationmentioning

confidence: 99%

“…*¯ *t + * *x j (¯ ũ j ) = 0 (1) * *t (¯ ũ i )+ * *x j (¯ ũ iũ j +p i j ) = *¯ i j *x j − * *x j (¯ ( i j ) sfs ) (2) and * *t (¯ Ẽ )+ * *x j (¯ Hũ j ) = * *x j (˜ i jũi )− *q j *x j (3) where , u i , p, T , E, H , i j , ( i j ) sfs , q i , are the density, velocity vector, pressure, temperature, total energy, total enthalpy, viscous stress tensor, subfilter scale turbulent stress tensor, total heat flux, respectively. In these equations, the viscous tensor i j takes the usual form…”

Section: Mean Flow Equationsmentioning

confidence: 99%

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An efficient numerical method for RANS/LES turbulent simulations using subfilter scale stress transport equations

Chaouat

2010

Numerical Methods in Fluids

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SUMMARYWe propose a numerical method for performing hybrid non-zonal RANS/LES simulations by using a subfilter scale stress transport model in the framework of finite volume technique. The turbulent equations are derived from the new partial integrated transport modeling (PITM) method. The PITM method has been initially developed for devising subfilter energy models based on the viscosity concept (Theoretical . The numerical method put in place is developed in a general framework of large eddy simulations and can be applied to almost all subfilter scale models based on transport equations of subfilter scale turbulent quantities. In this work, we have developed specific numerical schemes for solving the turbulent transport equations of compressible flows including the density, velocity, energy, subfilter scale turbulent stresses and subfilter scale dissipation rate that are strongly coupled together. When performing LES or VLES simulations, this coupling between the motion and turbulent equations poses some numerical problems because the subfilter scale turbulent stresses and dissipation rate are more fluctuating in time and space than in the case of RANS computations, so that a specific numerical treatment has been proposed. In this framework, new implicit iterative algorithms in time are especially developed for solving the unsteady equations of the turbulent energy, stresses and dissipation rate by ensuring the positivity of the normal stresses at each step of the computation. We show that the convective fluxes resulting from the volume technique including the main and turbulent variables can be computed by an approximate Riemann solver using new tensorial operators. The numerical solver is calibrated on the decay of isotropic spectrum and on the well-known fully turbulent channel flow for assessing the performances of the numerical method. Then, we perform numerical simulations of the turbulent channel flow over periodic hills on coarse and medium grids. This flow encountered in aeronautical applications is of complex physics as it is governed by interacting turbulence mechanisms associated with separation, recirculation and reattachment. As a result, it is found that the proposed numerical method used in conjunction with the subfilter stress model performs fairly well with these turbulent flows on different grids. From a practical point of view, this numerical method can be easily implemented in CFD codes for tackling engineering applications.

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