Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil


  •   Md. Abdus Salam

  •   Vikram Deshpande

  •   Nafiz Ahmed Khan

  •   M. A. Taher Ali


The moving surface boundary control (MSBC) has been a Centre stage study for last 2-3 decades. The preliminary aim of the study was to ascertain whether the concept can improve the airfoil characteristics. Number of experimental and numerical studies pointed out that the MSBC can superiorly enhance the airfoil performance albeit for higher velocity ratios (i.e. cylinder tangential velocity to free stream velocity). Although abundant research has been undertaken in this area on different airfoil performances but no attempt was seen to study effect of MSBC on NACA0021 airfoil for and also effects of lower velocity ratios. Thus, present paper focusses on numerical study of modified NACA 0021 airfoil with leading edge rotating cylinder for velocity ratios (i.e.) between 1 to 1.78 at different angles of attack. The numerical study indicates that the modified airfoil possess better aerodynamic performance than the base airfoil even at lower velocity ratios (i.e. for velocity ratios 0.356 and beyond). The study also focusses on reason for improvement in aerodynamic performance by close look at various parameters.

Keywords: velocity ratio, Moving surface boundary layer control, coefficient of lift, coefficient of drag, coefficient pressure


V.J. Modi, “Moving surface boundary layer control: a review,” Journal of Fluids and Structures, vol. 11, no. 6, pp. 627-663, Aug 1997.

V. J. Modi, “On the moving surface boundary-layer control”, In Fluids 2000 Conference and Exhibit, pp. 2238. Jun 2000.

V.R. Den Hartog, “Moving surface boundary layer control with application to autonomous underwater vehicles,” M.A.Sc. Thesis, Dept. Mech. Eng., University of British Columbia, Vancouver, Canada, 1999.

V.J. Modi and B. Triplett, “Moving surface boundary layer control for aircraft operation at high angles of attack,” presented at 41st Aerospace Sciences Meeting, Reno, Nevada, USA, Jan 2003.

V.J. Modi and B. Deshpande, “A Joukowski Airfoil with momentum injection,” AIAA article, pp. 4108, 2000.

V. J. Modi, M. S. U. K. Fernando, and T. Yokomizo. “Moving surface boundary-layer control as applied to two-dimensional and three-dimensional bluff bodies,” Journal of Wind Engineering and Industrial Aerodynamics, vol. 38, no. 1, pp. 83-92, 1991.

V.J., Modi and T. Yokomizo, “Pressure distribution on a roof in presence of the moving surface boundary layer control,” Journal of Visualization, vol. 1, no. 3, pp. 255-260, 1999.

V.J Modi., S.R. Munshi, G. Bandyopadhyay, and T. Yokomizo, “High performance airfoil with moving surface boundary layer control,” Journal of Aircraft, vol. 35, no.4, pp. 544-553, 1998.

S. Ahmed, A. Nazari and E. Wahba, “Numerical analysis of separation control over an airfoil section,” International Review of Aerospace Engineering, vol. 7, no. 3, pp. 61-68, 2014.

D. N. Welsh, M. Lester, M. Lopes, R. Gates and J. Hoover, “The effects of a leading-edge rotating cylinder on the performance of a NACA 0015 airfoil at high angles of attack,” AIAA Atmospheric Flight Mechanics Conference, pp. 0540.

M. N. Huda, T. Ahmed, T. S. M. Ahmed, M. A. Salam, M. R. Afsar, K. M. Faisal and M. A. T. Ali, “Study of NACA 0010 symmetric airfoil with leading edge rotating cylinder in a subsonic wind tunnel,” presented at 11th International Conference on Mechanical Engineering, BUET, Dhaka, Bangladesh, 2015.

K. M. Faisal, M. A. Salam, M. A. T. Ali, M. S. Sarkar, W. Safa and N. Sharah, “Flow control using moving surface at the leading edge of aerofoil”, Journal of Mechanical Engineering, vol. 47, no. 1, pp. 45 – 50, 2017.

N. A. Najdat and F. H. Mustafa, “Effect of gap between airfoil and embedded rotating cylinder on the airfoil aerodynamic performance,” Res Dev Material Sci., vol. 3, no. 4, pp. 1 – 10, 2018.

G. M. Gregorek, M. J. Hoffmann, and M. J. Berchak, “Steady state and oscillatory aerodynamic characteristics of a NACA 0021 airfoil: data report,” Ohio State University, Columbus, Ohio, USA.

W.P. Wolfe, S.S. Ochs, “Predicting aerodynamic characteristic of typical wind turbine airfoils using CFD”, no. SAND-96-2345. Sandia National Labs., Albuquerque, NM (United States), 1997.


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How to Cite
Salam, M.A., Deshpande, V., Khan, N. and Ali, M.A.T. 2019. Numerical Analysis of Effect of Leading-Edge Rotating Cylinder on NACA0021 Symmetric Airfoil. European Journal of Engineering and Technology Research. 4, 7 (Jul. 2019), 11-17. DOI: