Numerical Study of the Effect of Passive Counter Rotating Vanes Vortex Generator on NACA 2412 Airfoil

Authors

1 MSc Graduate

2 Mechanical Eng. Dept., Ferdowsi University of Mashhad

Abstract

The present study aim is to improve the performance of NACA2412 airfoil. For this purpose, the vortex generator is a type of counter rotating vanes in the passive mode used to convert the laminar flow to turbulent . This study was performed in three different locations on 20%, 30% and 40% airfoil length and at five different heights, 0.2, 0.4, 0.6, 0.8 and 1 times the thickness of the boundary layer. First by using numerical simulation on airfoil Without vortex generator with DES turbulence model, the Lift and Drag forces and flow characteristics such as the location of the separation point and the thickness of the boundary layer were calculated. The vortex generator is simulated on the airfoil with the SDES turbulence model. The results obtained from numerical simulations show a decrease in Flow separation on the airfoil. Also, in the case where the vortex generator is located at 20% of the chord length, the stall angle has been increased from 15 to 17 degree. If the height of the vortex generator is equal to the thickness of the boundary layer, the lift to drag ratio increased by 233.03%. But in the same case, the generator causes a 37.18% reduction in the lift to drag ratio for the zero degree attack angle. At low angles of attack, the vortex generator has an adverse effect, but at high angles of attack, if the vortex generator is placed before the separation point on the airfoil, it has a significant effect.

Keywords

References

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Journal of Solid and Fluid Mechanics
Volume 11, Issue 6
January and February 2022
Pages 235-252

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