Simulation of leading edge rotation of NACA 0012 airfoil to control separation

N. Ahmed*, B. S. Yilbas, M. O. Budair

*Corresponding author for this work

Research output: Contribution to conferencePaperpeer-review


Numerical simulation of flow past airfoils is important in the aerodynamic design of aircraft wings and turbomachinery parts. These lifting devices often obtain optimum performance at the condition of onset of separation. In the present study, numerical simulation of steady flow over NACA 0012 airfoil is accomplished employing control volume approach. The flow field is determined by solving two-dimensional incompressible Navier-Stokes equations while the effect of turbulence are accounted for by the k-ε model. The study is extended to include effect of leading edge rotation on the initiation of point of separation. The pressure, lift, and drag coefficients are computed for different speed of leading edge rotation and angle of attack. It is found that leading edge rotation reduces the wake size at high angle of attack. In addition, increase in the lift and decrease in the drag coefficients are observed.

Original languageEnglish
Number of pages7
StatePublished - 1997

ASJC Scopus subject areas

  • General Engineering


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