Simulations of Separated Flow around an Airfoil with Ice Shape using Hybrid RANS/LES Models

Alam, Mohammad Faridul; Walters, D. Keith; Thompson, David S.

doi:10.2514/6.2011-3972

Cited by 8 publications

(3 citation statements)

References 24 publications

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“…They also found a strong effect (with a variance of 95%) of the spanwise variation in the geometry on lift coefficients for angle of attack in the range 5 o − 15 o . In a recent review paper, Stebbins et al [49] made a comprehensive assessment of RANS [50,51,52] and HRL methods [53,54,55] in the study of horn geometry and concluded that the results of HRL methods are more accurate than RANS solutions, particularly at high angles of attack, owing to the ability of LES-based methods to capture the unsteadiness of the flow. Still, they displayed discrepancies with the experimental data.…”

Section: Introductionmentioning

confidence: 99%

Large-eddy simulations of the flow on an aerofoil with leading-edge imperfections

Kumar

Piomelli

Lehmkuhl

2021

Journal of Turbulence

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We performed large-eddy simulations of the flow over an airfoil to understand the effects of leading-edge roughness designed to mimic ice accretion. The roughness elements protrude outside the boundary layer, which, near the leading edge, is very thin; thus, the configuration does not represent a classical rough-wall boundary layer, but rather the flow over macroscopic obstacles. A grid convergence study is conducted and results are validated by comparison to numerical and experimental studies in the literature. The main effect of the obstacles is to accelerate transition to turbulence. Significant variations in structure generation are observed for different roughness shapes. The three-dimensionality of the irregularities has a strong impact on the flow: it creates alternating regions of high-speed ("peaks") and lowspeed ("valleys") regions, a phenomenon termed "channelling". The valley regions resemble a decelerating boundary layer: they exhibit considerable wake and higher levels of Reynolds stresses. The peak regions, on the other hand, are more similar to an accelerating one. Implications of the channelling phenomenon on turbulence modelling are discussed.

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Section: Introductionmentioning

confidence: 99%

Large-eddy simulations of the flow on an aerofoil with leading-edge imperfections

Kumar

Piomelli

Lehmkuhl

2021

Journal of Turbulence

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“…Despite the capability of the Direct Numerical Simulation to obtain the resolution of the space and time scales, it requires enormous computing capability [24]. Thus, it is too costly for users [25]. Likewise, large eddy simulation is computationally expensive for complex unsteady phenomena because of the 3D nature of the eddies [24,25].…”

Section: Introductionmentioning

confidence: 99%

“…Thus, it is too costly for users [25]. Likewise, large eddy simulation is computationally expensive for complex unsteady phenomena because of the 3D nature of the eddies [24,25]. However, CFD solutions that are feasible and economical for low-Reynolds-number flows are rare [7].…”

Section: Introductionmentioning

confidence: 99%

Laminar Separation Bubble and Flow Topology of NACA 0015 at Low Reynolds Number

Ibren

Andan

Asrar

et al. 2021

CFDL

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The development of sophisticated unmanned aerial vehicles and wind turbines for daily activities has triggered the interest of researchers. However, understanding the flow phenomena is a strenuous task due to the complexity of the flow field. The engaging topic calls for more research at low Reynolds numbers. The computational investigations on a two-dimensional (2D) airfoil are presented in this paper. Numerical simulation of unsteady, laminar-turbulent flow around NACA 0015 airfoil was performed by using shear-stress transport (SST) model at relatively low Reynolds number (8.4 × 104 to 1.7 × 105) and moderate angles of attack (0 ≤ α ≤ 6). In general, on the suction side, with increasing Reynolds number and angles of attack, separation, and reattachment point shifts upstream and concurrently shrinking the size of the laminar bubble. However, On the pressure side, the laminar bubble is seen to move toward the trailing edge at the relatively same size as the angle of attack increases. Moreover, the variations in the angle of attack have more influence on the laminar separation bubble characteristics as compared to the Reynolds number. The reattachment points were barely observed for the range of the angles of attack studied. At very high angles of attack, it is recommended to simulate the flow field using large eddy simulation or direct numerical simulation since the flow is considered three-dimensional and detached from the surface thus forming a complex phenomenon.

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Laminar, Turbulent, and Transitional Simulations in Benchmark Cases with Cardiovascular Device Features

Bhushan

Walters

Burgreen

2013

Cardiovasc Eng Tech

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Simulations of Separated Flow around an Airfoil with Ice Shape using Hybrid RANS/LES Models

Cited by 8 publications

References 24 publications

Large-eddy simulations of the flow on an aerofoil with leading-edge imperfections

Large-eddy simulations of the flow on an aerofoil with leading-edge imperfections

Laminar Separation Bubble and Flow Topology of NACA 0015 at Low Reynolds Number

Laminar, Turbulent, and Transitional Simulations in Benchmark Cases with Cardiovascular Device Features

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