Numerical simulation of active flow control to airfoil stall using local synthetic jet

By introducing local synthetic jet control to the flow over airfoil, separation control can be implemented with low energy cost. The time-accurate Reynolds-averaged Navicr-Stokes equations are solved by a finite-volume scheme using preconditioned multigrid acceleration and a fully implicit 'dual time method' with Newton-like LU-SGS sub-iterations. An efficient and robust numerical method and computer code are developed to simulate the active stall control on airfoil. The numerical example, the active flow control on a TAU0015 airfoil, shows that the stall characteristics can be significantly improved by forcing zcro-mass-flux jet on the leading edge of airfoil. The computational results are compared with Seifert's experimental data and good agreement has been achieved. Parameter study is also conducted to show the effects of blowing momentum coefficient, forcing frequency, and jet angle on the aerodynamic performance.