Numerical study of the aerodynamic performance of blunt trailing-edge airfoil considering the sensitive roughness height

2017 ◽  
Vol 42 (29) ◽  
pp. 18252-18262 ◽  
Author(s):  
Xu Zhang ◽  
Gege Wang ◽  
Mengjie Zhang ◽  
Hailong Liu ◽  
Wei Li
Keyword(s):  
Numerical Study ◽  
Aerodynamic Performance ◽  
Roughness Height ◽  
Trailing Edge ◽  
Blunt Trailing Edge

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

Numerical study of improving aerodynamic performance of low solidity LPT cascade through increasing trailing edge thickness

2016 ◽  
Vol 25 (4) ◽  
pp. 342-348 ◽  
Author(s):  
Chao Li ◽  
Peigang Yan ◽  
Xiangfeng Wang ◽  
Wanjin Han ◽  
Qingchao Wang
Keyword(s):  
Numerical Study ◽  
Aerodynamic Performance ◽  
Trailing Edge

Numerical Study on Three-Dimensional Optimization of a Low-Speed Axial Compressor Rotor

2014 ◽  
Author(s):  
Chenkai Zhang ◽  
Jun Hu ◽  
Zhiqiang Wang ◽  
Chao Yin ◽  
Wei Yan
Keyword(s):  
Numerical Optimization ◽  
Large Scale ◽  
Numerical Study ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Compressor Rotor ◽  
Flow Loss

This paper presents numerical optimization of a compressor rotor, to deepen the knowledge of endwall flow in the large-scale axial subsonic compressor, accordingly reduce its endwall loss and improve its aerodynamic performance. With numerical simulation and numerical optimization tools, three-dimensional stacking principle is optimized to improve the design operation point performance for the rotor. Results show that, hub region of the rotor cannot undertake large blade loading; compared to the prototype rotor, obvious aerodynamic performance improvements locate near the hub area, and a certain degree of positive dihedral in this region effectively helps to reduce its flow loss. The effect of “loaded leading edge and unloaded trailing edge” due to positive dihedral was shown, which suppresses flow separation near the trailing edge, consequently obviously reduces the flow loss and largely improves the rotor aerodynamic performance.

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