Investigation of the dynamic stall about the pitching airfoil
等速上仰翼型动态失速现象研究

The static stall about the airfoil at the high angle of attack deteriorate the characteristics of aerodynamics rapidly. But this phenomena can be delayed effectively by the dynamic stall caused by the unsteady motion. The dual-step Roe schema developed by Rogers was used to solve the incompressible Navier-Stokes equations. Computationally simulated the dynamic stall about the pitching NACA0015 airfoil with identical pitching rate ($\alpha =0^{\circ} \sim 60^{\circ})$, at Low Reynolds number ($Re=4.8 \times 10^{4}$). And compared with Walker's experimental results to correct the CFD results. The developments of the main vortex, the second vortex and the third vortex, and the lift coefficient alteration to the angle of attack during the process were studied. Finally, the effects of the different pitching rate to the dynamic stall were compared.