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Large Eddy Simulation of Flow Separation Control over a NACA2415 Airfoil

Authors: M. Tahar Bouzaher

Abstract:

This study involves a numerical simulation of the flow around a NACA2415 airfoil, with a 15°angle of attack, and flow separation control using a rod, It reposes inputting a cylindrical rod upstream of the leading edge in order to accelerate the transition of the boundary layer by interaction between the rod wake and the boundary layer. The viscous, non-stationary flow is simulated using ANSYS FLUENT 13. Our results showed a substantial modification in the flow behavior and a maximum drag reduction of 51%.

Keywords: CFD, Flow separation, Active control, Boundary layer, rod, NACA 2415.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1337167

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References:


[1] Serdar Genc, M., Hakan,kAcıkel, H. An experimental study on aerodynamics of NACA2415 aerofoil at low Re numbers Journal of Experimental Thermal and Fluid Science: 10.1016.
[2] Mittal R., Kotapati R.B. et Cattafesta L. 2005. "Numerical study of resonant interactions and flow control in a canonical separated flow". AIAA Paper, No. 2005-1261.
[3] Greenblatt D, Wygnanski IJ. The control of flow separation by periodic excitation. Prog Aerospace Sci 2000;36:487–545.
[4] amotsu Igarashi. (1997) "Drag reduction of a square prism by flow control using a small rod”. Journal of Wind Engineering and Industrial Aerodynamics; 69 71 141-153.
[5] Igarashi, T., Nobuaki, T.Drag reduction of flat plate normal to airstream by flow control using a rod .Journal of Wind Engineering and Industrial Aerodynamics 90 (2002) 359–376.
[6] T. Sutsui, Igarashi, T. Drag reduction of a circular cylinder in an air-stream Journal of Wind Engineering and Industrial Aerodynamics 90 (2002) 527–541.