An investigation of interface conditions inherent in detached-eddy simulation methods

Zhou, Lingjun; Zhao, Rui; Yuan, Wu

doi:10.1016/j.ast.2018.01.005

Cited by 13 publications

(2 citation statements)

References 16 publications

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“…The numerical simulation in this study was conducted using an in-house code, which has been examined by plentiful studies and could acquire satisfying results in various flows, such as supersonic cavity flow and SWBLIs [25,30,34]. In the calculation process, the inviscid fluxes were discretized and reconstructed by Roe scheme with a second-order monotone upstream-centered schemes for conservation laws (MUSCL), and the central difference method was used for the discretization of viscous fluxes.…”

Section: Computational Detailsmentioning

confidence: 99%

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Zhang

Zeng

et al. 2022

Aerospace

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Shock wave-boundary layer interactions (SWBLIs) have a tremendous influence on the performance of hypersonic vehicles. For the numerical simulation of such engineering flows, Reynolds averaged Navier-Stokes (RANS) still occupies an irreplaceable role. However, parameters of turbulence models in RANS have substantial uncertainties, which impact the reliability of simulation results. Thus, the aim of the present study is to conduct an uncertainty analysis on parameters in the shear-stress transport (SST) turbulence model for the simulation of SWBLIs. In the current work, uncertainty quantification was performed first. A surrogate model was constructed by the non-intrusive polynomial chaos (NIPC) method to propagate uncertainties from model parameters to the quantities of interests (QoIs) and quantify them. In the subsequent sensitivity analysis, the key parameters were identified for such flow by calculating the Sobol index of each parameter for various QoIs. The results indicate that uncertainties of model parameters led to non-negligible uncertainties in those QoIs, particularly in skin friction and wall heat flux. The parameters α1, σω1, β1 were identified as primary contributors through the sensitivity analysis. Moreover, the specific effects of the three parameters on the flow prediction were analyzed by changing the parameters’ values separately.

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Section: Computational Detailsmentioning

confidence: 99%

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Zhang

Zeng

et al. 2022

Aerospace

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“…Researchers throughout the world have been conducting substantial research to prevent or postpone boundary layer separation and improve airfoil efficiency [7]. One such area of research is the use of suction or the blowing of turbulent air via suction holes in the airfoil [8].…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Streamline on Aerofoil with Suction Hole in Wind Tunnel

Basnayake Mudiyanselage Sachinthana Bandara Moonamale,

Syahrullail Samion,

Mohamad Nor Musa

et al. 2024

AREFMHT

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This study looks into the impact of pressure suction holes in the NACA 0012 airfoil on aerodynamic performance. The goal is to use wind tunnel tests to compute the lift and drag forces for the NACA 0012 airfoil with suction holes at various air speeds and angles of attack. The relationship between air speed, angle of attack, drag coefficient, and lift coefficient will be determined by analysing the obtained data. The goal of the research is to better understand the flow patterns and variations in streamlines of the NACA 0012 airfoil at different velocity and attack angles. The test model will use the NACA 0012 airfoil, which is recognised for its symmetrical shape. Suction holes, varying from one to four, will be installed to provide insight into the influence of pressure suction on the boundary layer and streamline behaviour of the airfoil. The study will be carried out in a low-speed wind tunnel within the Fluid Mechanics laboratory, with the streamlines visualised using a smoke generator. This study is significant because it contributes to our understanding of flow characteristics, pressure distributions, and boundary layer control in aerodynamic design. It also provides excellent exposure to wind tunnel testing procedures, aviation industry practises, and continuing airfoil design research. This study adds to the body of knowledge on optimising airfoil performance by evaluating the effect of pressure suction holes on the NACA 0012 airfoil. The findings will be useful to researchers, aerodynamic enthusiasts, and aviation experts, allowing them to further investigate the potential benefits of pressure suction techniques in improving airfoil efficiency and performance.

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Effect of von Karman length scale in scale adaptive simulation approach on the prediction of supersonic turbulent flow

Zhang

et al. 2019

Aerospace Science and Technology

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An investigation of interface conditions inherent in detached-eddy simulation methods

Cited by 13 publications

References 16 publications

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Evaluation of Streamline on Aerofoil with Suction Hole in Wind Tunnel

Effect of von Karman length scale in scale adaptive simulation approach on the prediction of supersonic turbulent flow

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