engleski

Numerical Prediction of Airfoil Stall

Prediction of the airfoil characteristics, particularly for large incidence angles when stall occurs, depends on the prediction of separation. Turbulent flow around NACA 0012 airfoil in the range of incidence angles from 0.0 up to stall angle at Re=2.8 106 is calculated by applying the finite volume method with modified turbulence model. A grid independent solution is achieved on the C-type grid around airfoil with 1664*320 control volumes for the finest grid in multigrid procedure. Inclusion of the laminar part by prescribing transition is required in order to bring the calculated data closer to the experimental ones. Very good agreement is obtained between the calculated and the experimental values of the lift-drag coefficients and the pressure coefficient distribution at moderate incidence angles. The peak values of the lift coefficient in the stall area are underpredicted. Trailing edge separation bubble appears at 180.

airfoil; stall; lift/drag; modeling

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