Numerical Simulation of Iced Wing Using Separating Shear Layer Fixed Turbulence Models

Li, Haoran; Zhang, Yufei; Chen, Haixin

doi:10.2514/1.j060143

Cited by 14 publications

(4 citation statements)

References 30 publications

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“…If 𝑓 𝑁𝐸 = 1, the model reverts to the original k − 𝑣 2 − 𝜔 model. In previous work [27,28], the shear layer region where 𝑃 𝑣 2 /𝜀 > 2.5 is located by the switch function Γ 𝑆𝑆𝐿 , which means that the modification term 𝑓 𝑁𝐸 is turned off where 𝑃 𝑣 2 /𝜀 is less than 2.5. The 𝑅𝑒 𝛺 term in Eq.…”

Section: B the Spf 𝒌 − 𝒗 𝟐 − 𝝎 Modelmentioning

confidence: 99%

“…[29] and Li et al [27,28] found that 𝑃 𝑘 /𝜀 can be greater than 1.8 in the nonequilibrium turbulence region. 𝑃 𝑘 tends to be significantly larger than ε and often as much as 3-4 times greater in a separated shear layer.…”

Section: B the Spf 𝒌 − 𝒗 𝟐 − 𝝎 Modelmentioning

confidence: 99%

“…For example, Fang et al [26] found that nonequilibrium turbulence is obvious in the regions of the corner separation, wake, and boundary layer of the compressor flow. Recently, Li et al [27,28]…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Prediction of High-Lift Configuration Using k−v2¯−ω Turbulence Model

Zhang

et al. 2022

AIAA Journal

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The aerodynamic performance of the high-lift configuration greatly influences the safety and economy of commercial aircraft. Accurately predicting the aerodynamic performance of the high-lift configuration, especially the stall behavior, is important for aircraft design. However, the complex flow phenomena of high-lift configurations pose substantial difficulties to current turbulence models. In this paper, a three-equation 𝒌 − 𝒗 𝟐 ̅̅̅ − 𝝎 turbulence model for the Reynolds-averaged Navier-Stokes equations is used to compute the stall behavior of high-lift configurations. A separated shear layer fixed function is implemented in the turbulence model to better capture the nonequilibrium characteristics of turbulence. Different high-lift configurations, including the two-dimensional multielement NLR7301 and Omar airfoils and a complex full-configuration model (JAXA Standard Model), are numerically tested. The results indicate that the effect of the nonequilibrium characteristics of turbulence is significant in the free shear layer, which is key to accurately predicting the stall behavior of high-lift devices. The modified SPF 𝒌 − 𝒗 𝟐 ̅̅̅ − 𝝎 model is more accurate in predicting stall behavior than the Spalart-Allmaras, shear stress transport, and original 𝒌 − 𝒗 𝟐 ̅̅̅ − 𝝎 models for the full high-lift configuration. The relative errors in the predicted maximum lift coefficients are within 3% of the experimental data. Nomenclature AOA = angle of attack, deg

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Section: B the Spf 𝒌 − 𝒗 𝟐 − 𝝎 Modelmentioning

confidence: 99%

Section: B the Spf 𝒌 − 𝒗 𝟐 − 𝝎 Modelmentioning

confidence: 99%

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Aerodynamic Prediction of High-Lift Configuration Using k−v2¯−ω Turbulence Model

Zhang

et al. 2022

AIAA Journal

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“…Therefore, understanding the precise law of convective heat transfer in the boundary layer of the airframe is a technical prerequisite for the development of an efficient full airfoil anti-icing system [2]. The study of convective heat transfer requires experimental or simulation methods to obtain the evolution of the velocity and temperature fields [3][4][5], but the boundary layer pattern calculated by simulation methods is often a uniform transition [6], which does not reflect the relationship between heat transfer and the flow regime. However, in numerous previous studies, it was found that the effect of heat transfer on the airfoil surface would be influenced by the airfoil flow pattern, and that heating at different regions of the airfoil would have different effects on the flow field and heat transfer efficiency [7].…”

Section: Introductionmentioning

confidence: 99%

Experimental research on effect of zonal heating airfoil about boundary layer flow and heat transfer

Dong

Sang

Yang

et al. 2023

J. Phys.: Conf. Ser.

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The anti-icing of aircraft and large wind turbines, where the wall temperature is higher than the fluid temperature, can significantly alter the flow evolution characteristics of the boundary layer. Local heating strategies for the manifold state need to be designed based on the changing characteristics of the flow velocity and temperature field in order to precisely control the heat supply and reduce inefficient energy consumption. In order to obtain accurate heat transfer characteristics of the airfoil’s boundary layer flow, it is necessary to refine the measurement of the boundary layer characteristics during flow and heat transfer. In this paper, wind tunnel experiments are carried out on the NACA2412 model with full surface’s zonal electric heating. The wall surface is equipped with a built-in heater and the temperature of the wall surface is obtained through the corresponding temperature sensor. By studying layer characteristics of the four heated regions, namely the laminar flow region near leading edge, the laminar flow destabilisation region, the transition region and the fully turbulent flow region, and comparing them with the boundary layer characteristics of the unheated airfoil, the effects of the presence of heat sources in different regions on the stability of the flow field and the spatial heat transfer pattern are revealed. The results show that heating in the laminar and turbulent zones maintains the stability of the flow field to a greater extent and achieves better heat transfer strength, while heating in the unstable zone brings forward the turbulence and heating in the fully turbulent zone intensifies the flow separation at the trailing edge of the airfoil. This study can be used as a reference for the design of efficient anti-icing systems on full wing surfaces.

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Effects of simplified horn ice shapes on flow structures around an airfoil

Zheng,

Jin,

et al. 2024

Acta Mech. Sin.

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Numerical Simulation of Iced Wing Using Separating Shear Layer Fixed Turbulence Models

Cited by 14 publications

References 30 publications

Aerodynamic Prediction of High-Lift Configuration Using k−v2¯−ω Turbulence Model

Aerodynamic Prediction of High-Lift Configuration Using k−v2¯−ω Turbulence Model

Experimental research on effect of zonal heating airfoil about boundary layer flow and heat transfer

Effects of simplified horn ice shapes on flow structures around an airfoil

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