Numerical simulation of the effect of relative thickness on aerodynamic performance improvement of asymmetrical blunt trailing-edge modification

2015 ◽  
Vol 80 ◽  
pp. 489-497 ◽  
Author(s):  
Xu Zhang ◽  
Wei Li ◽  
Hailong Liu
Keyword(s):  
Numerical Simulation ◽  
Performance Improvement ◽  
Aerodynamic Performance ◽  
Relative Thickness ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Edge Modification

scholarly journals The Effect of Gurney Flap and Trailing-edge Wedge on the Aerodynamic Behavior of an Axial Turbine Blade

2021 ◽  
Vol 2 (4) ◽  
pp. 293-305
Author(s):  
Mohammad Mahdi Mahzoon ◽  
Masoud Kharati-Koopaee
Keyword(s):  
Angle Of Attack ◽  
Vortex Generator ◽  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Gurney Flap ◽  
Maximum Increment ◽  
Lift And Drag ◽  
Lift And Drag Coefficient

In this research, the effect of Gurney flap and trailing-edge wedge on the aerodynamic behavior of blunt trailing-edge airfoil Du97-W-300 which is equipped with vortex generator is studied. To do this, the role of Gurney flap and trailing-edge wedge on the lift and drag coefficient and also aerodynamic performance of the airfoil is studied. Validation of the numerical model is performed by comparison of the obtained results with those of experiment. Results show that before stall, Gurney flap leads to the increase in the aerodynamic performance in a wider range of angle of attack. Numerical findings reveal that the maximum increment for the aerodynamic performance is obtained at low angle of attack when trailing-edge wedge is employed. It is found that for the highest considered value of Gurney flap and trailing-edge wedge heights, where the highest values for the lift occur, the higher aerodynamic performance at low angle of attack is obtained when trailing-edge wedge is used and at high angle of attack, the Gurney flap results in a higher aerodynamic performance. It is also shown that when high aerodynamic performance is concerned, addition of Gurney flap to the airfoil leads to the higher value for the lift. Doi: 10.28991/HIJ-2021-02-04-03 Full Text: PDF

Aerodynamic Performance of Thick Blunt Trailing Edge Airfoils

2010 ◽  
Author(s):  
Aubryn Cooperman ◽  
Anthony McLennan ◽  
Jonathon Baker ◽  
C van Dam ◽  
Raymond Chow
Keyword(s):  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Blunt Trailing Edge

scholarly journals Aerodynamic and aeroacoustic behavior of span-wise wavy trailing edge modified SNL 100 m blade

2018 ◽  
Vol 43 (1) ◽  
pp. 4-25 ◽  
Author(s):  
Seung Joon Yang ◽  
James D Baeder
Keyword(s):  
Numerical Simulation ◽  
Parametric Study ◽  
Graphics Processing Unit ◽  
Navier Stokes ◽  
Processing Unit ◽  
Detached Eddy Simulation ◽  
Trailing Edge ◽  
Wind Speeds ◽  
Eddy Simulation ◽  
Edge Modification

The aerodynamic and aeroacoustic behaviors of wavy trailing edge modified flatback wind turbine blade have been investigated through numerical simulation. Previous studies have demonstrated aerodynamic and aeroacoustic benefits of the span-wise wavy trailing edge modification on the flatback trailing edge. The previous two-dimensional airfoil test cases have been extended to a complete set of design parametric study. Aerodynamic and aeroacoustic characteristics of the parametric study have been discussed, relying on the wave size, including recently added cases. Furthermore, in the current study, the wavy trailing edge modification has been applied to the Sandia flatback blade called “SNL100-03FB” and tested in rotating blade conditions. Several variations of the wavy trailing edge design have been tested for a range of wind speeds using an overset computation domain. The numerical simulation employs the in-house developed Navier–Stokes solver, OVERTURNS, as well as Graphics Processing Unit (GPU)-accelerated solver, GPURANS3D. Both are hybrid Reynolds Averaged Navier Stokes (RANS)/Large Eddy Simulation (LES) simulation; delayed detached eddy simulation has been used with the Spalart–Allmaras turbulent model and modified [Formula: see text] laminar–turbulent transition model.

Sign in / Sign up

Export Citation Format

Share Document