Verification of the Shear-Stress Transfer Model and its Modifications in the Calculation of a Turbulent Flow Around a Semicircular Airfoil with a Zero Angle of Attack

Исаев, С. А.; Baranov, P. A.; Zhukova, Yu. V.; Kalinin, E. I.; Miau, Jiun‐Jih

doi:10.1007/s10891-016-1354-3

Cited by 8 publications

(7 citation statements)

References 35 publications

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“…Therefore, when the first model is used, vortex viscosity does not increase in the cores. At the same time, as confirmed by numerous tests [21,22] , the use of the SST model [19] yields a false eddy viscosity increase in the core of largescale vortices and a very high eddy viscosity level as a whole. To avoid a non-physical eddy viscosity increase, this became possible within the generalized Rodi-Leschziner-Isaev (RLI) approach [15] with the correction for eddy viscosity computed by the SST model [19] with the correction function of the turbulent Richardson number when the value of Isaev-Kharchenko-Usachov's semiempirical constant С c = 0.02 is taken instead of 0.1 [17] in the correction for the two-parameter dissipative model.…”

Section: Introductionmentioning

confidence: 82%

“…The Reynolds number is assumed to be equal to 50 0 0 0. As in [3,22] , to solve the problem on two-dimensional unsteady turbulent incompressible viscous fluid flow around the semi-circular profile, the mathematical model based on the system of the unsteady Reynolds-averaged Navier-Stokes (URANS) equations is used.…”

Section: Numerical Simulation Problem Turbulence Modelsmentioning

confidence: 99%

“…Undisturbed flow parameters are assigned at the computational domain inlet. Turbulence characteristics are determined in the same manner as in [3,10,15,22] for the conditions of wind tunnel experiments. So, the turbulence energy k ∞ at the domain inlet is assigned in terms of the incoming flow turbulence intensity Tu ∞ = 1.5% and the turbulence scale l ∞ is chosen from the condition when eddy viscosity is close to physical one.…”

Section: Numerical Simulation Problem Turbulence Modelsmentioning

confidence: 99%

“…The center of the Cartesian х , у coordinate system is located in the center of the profile base. The grid is the analog of the О-type grid [3,22] with a decreased nearwall grid step equal to 10 −5 . The number of О-type grid cells surrounding the profile in the vertical direction is 50.…”

Section: Grids and Their Classificationmentioning

confidence: 99%

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Numerical simulation and experiments on turbulent air flow around the semi-circular profile at zero angle of attack and moderate Reynolds number

et al. 2019

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Two-dimensional flow around a semi-circular profile at the zero angle of attack and at Re = 50000 on the self-oscillatory period is extensively studied by the URANS method involving the standard semi-empirical SST turbulence models, the SST turbulence model with the correction for streamline curvature modified within the Rodi-Leschziner-Isaev and Smirnov-Menter approaches, as well as involving Hanjalic's four-parameter eddy viscosity elliptic relaxation model and its analog-eddy viscosity elliptic blending model proposed in the present work. This has been done with the use of different-structure grids (multiblock with structured overlapping and unstructured composite). Different numerical approximation methods realized in six codes (VP2/3, SigmaFlow, Fluent, CFX, OpenFOAM, and StarCCM+) are used. An underestimation (up to 30%) of time-averaged integral aerodynamic loads is revealed by means of the standard near-wall SST model. This is explained by the high vortex viscosity production in the profile wake. Wind tunnel tests show that the location of cutoff washers on the semi-circular profile provides a quasi-two-dimensional flow around it and allows applying measurement data to verify two-dimensional turbulent flow. The best agreement of experimental results and numerical predictions when comparing the Strouhal number and time-averaged surface pressure coefficient distributions is achieved using both the modified SST model with the correction for streamline curvature and the modified eddy viscosity elliptic blending model. When the SST model with the correction for streamline curvature, modified within the Rodi-Leschziner-Isaev, Smirnov-Menter and Durbin approaches, is used, all the above codes yield close predictions of a vertical aerodynamic load on the oscillation period.

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Section: Introductionmentioning

confidence: 82%

Section: Numerical Simulation Problem Turbulence Modelsmentioning

confidence: 99%

Section: Numerical Simulation Problem Turbulence Modelsmentioning

confidence: 99%

Section: Grids and Their Classificationmentioning

confidence: 99%

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Numerical simulation and experiments on turbulent air flow around the semi-circular profile at zero angle of attack and moderate Reynolds number

et al. 2019

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“…Approving and testing the RLI approach when comparing the numerical predictions obtained by different semi-empirical models and software with the experimental data were made to solve the traditional tasks of recirculating the flows, as well as of the flow and heat transfer control due to forming intense large-scale vortex structures [58][59][60][61][62][63][64][65][66][67][68][69][70][71][72][73][74][75][76][77]. The first group of tasks included recirculating flows in a square cavity with a movable cover [53] in a round cavity on the wall of the plane-parallel [53,58] and U-shaped [59,60,78] channels for the periodic flow around the airfoil NACA0012 when the angle of attack was varied from 0 • to 180 • [61].…”

Section: Introductionmentioning

confidence: 99%

Standard and Modified SST Models with the Consideration of the Streamline Curvature for Separated Flow Calculation in a Narrow Channel with a Conical Dimple on the Heated Wall

et al. 2021

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The testing of the standard and modified SST models of the transfer of shear stresses was carried out on an example of calculating the heat transfer with an intense detached flow around a conical dimple with a slope angle of 45° on the heated wall of a narrow channel. It was shown that the standard turbulence model by Menter SST (MSST) of 2003, widely used in the packages Fluent, CFX, StarCCM+, etc., significantly underestimated the intensity of the return flow. A correction of this model was presented that took into account the influence of the curvature of streamlines within the framework of the Rodi-Leshziner-Isaev (RLI) approach for spatial separated flows. It was found that the predictions for the RLI MSST 2003 were close to the predictions for the original standard MSST 1993, in which the eddy viscosity was calculated using the vorticity modulus. At the same time, the predictions based on the modified one, following Smirnov-Menter (SM) MSST 2003, included in the ANSYS model catalog did not differ too much from the standard MSST 2003. The preference of the MSST modified within the RLI 2003 for calculating the heat transfer in intense separated flows was substantiated.

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Improvement of aerodynamic characteristics of a thick airfoil with a vortex cell in sub- and transonic flow

et al. 2017

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Verification of the Shear-Stress Transfer Model and its Modifications in the Calculation of a Turbulent Flow Around a Semicircular Airfoil with a Zero Angle of Attack

Cited by 8 publications

References 35 publications

Numerical simulation and experiments on turbulent air flow around the semi-circular profile at zero angle of attack and moderate Reynolds number

Numerical simulation and experiments on turbulent air flow around the semi-circular profile at zero angle of attack and moderate Reynolds number

Standard and Modified SST Models with the Consideration of the Streamline Curvature for Separated Flow Calculation in a Narrow Channel with a Conical Dimple on the Heated Wall

Improvement of aerodynamic characteristics of a thick airfoil with a vortex cell in sub- and transonic flow

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