Leading edge vortex separation study by di[|#11#|]fferent vortex and flow separation identi[|#12#|]fication methods

2017 ◽  
Author(s):  
Yangzi Huang ◽  
Melissa A. Green
Keyword(s):  
Flow Separation ◽  
Leading Edge ◽  
Leading Edge Vortex ◽  
Vortex Separation ◽  
Edge Vortex

Three-Dimensional Solution of Flows over Wings with Leading-Edge Vortex Separation

AIAA Journal ◽  
1976 ◽  
Vol 14 (4) ◽  
pp. 519-525 ◽  
Author(s):  
James A. Weber ◽  
Guenter W. Brune ◽  
Forrester T. Johnson ◽  
Paul Lu ◽  
Paul E. Rubbert
Keyword(s):  
Three Dimensional ◽  
Leading Edge ◽  
Dimensional Solution ◽  
Leading Edge Vortex ◽  
Vortex Separation ◽  
Edge Vortex

Three-Dimensional Flow over Wings with Leading-Edge Vortex Separation

AIAA Journal ◽  
1980 ◽  
Vol 18 (4) ◽  
pp. 367-380 ◽  
Author(s):  
F. T. Johnson ◽  
E. N. Tinoco ◽  
P. Lu ◽  
M. A. Epton
Keyword(s):  
Three Dimensional ◽  
Leading Edge ◽  
Three Dimensional Flow ◽  
Leading Edge Vortex ◽  
Dimensional Flow ◽  
Vortex Separation ◽  
Edge Vortex

The effects of flow separation on a lambda wing aerodynamics

2019 ◽  
Vol 91 (8) ◽  
pp. 1100-1112 ◽  
Author(s):  
Mehdi Dadkhah ◽  
Mehran Masdari ◽  
Mohammad Ali Vaziri ◽  
Mojtaba Tahani
Keyword(s):  
Drag Coefficient ◽  
Turbulence Model ◽  
Flow Separation ◽  
Turbulence Models ◽  
Leading Edge ◽  
Pitching Moment ◽  
Aerodynamic Coefficients ◽  
Content Type ◽  
Leading Edge Vortex ◽  
Edge Vortex

Purpose In this paper, experimental and numerical results of a lambda wing have been compared. The purpose of this paper is to study the behaviour of lambda wings using a CFD tool and to consider different numerical models to obtain the most accurate results. As far as the consideration of numerical methods is concerned, the main focus is on the evaluation of computational methods for an accurate prediction of contingent leading edge vortices’ path and the flow separation occurring because of the burst of these vortices on the wing. Design/methodology/approach Experimental tests are performed in a closed-circuit wind tunnel at the Reynolds number of 6 × 105 and angles of attack (AOA) ranging from 0 to 10 degrees. Investigated turbulence models in this study are Reynolds Averaged Navior–Stokes (RANS) models in a steady state. To compare the accuracy of the turbulence models with respect to experimental results, sensitivity study of these models has been plotted in bar charts. Findings The results illustrate that the leading edge vortex on this lambda wing is unstable and disappears soon. The effect of this disappearance is obvious by an increase in local drag coefficient in the junction of inner and outer wings. Streamlines on the upper surface of the wing show that at AOA higher than 8 degrees, the absence of an intense leading edge vortex leads to a local flow separation on the outer wing and a reverse in the flow. Research limitations/implications Results obtained from the behaviour study of transition (TSS) turbulence model are more compatible with experimental findings. This model predicts the drag coefficient of the wing with the highest accuracy. Of all considered turbulence models, the Spalart model was not able to accurately predict the non-linearity of drag and pitching moment coefficients. Except for the TSS turbulence model, all other models are unable to predict the aerodynamic coefficients corresponding to AOA higher than 10 degrees. Practical implications The presented results in this paper include lift, drag and pitching moment coefficients in various AOA and also the distribution of aerodynamic coefficients along the span. Originality/value The presented results include lift, drag and pitching moment coefficients in various AOA and also aerodynamic coefficients distribution along the span.

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