Post-Stall Flow Control on an Airfoil Using Localized Jet Actuators

Active control of high angle-of-attack flow about a NACA0012 airfoil is numerically investigated using the Reynolds-averaged Navier-Stokes equations. The results of numerical simulations of both baseline and controlled cases are presented. In the baseline study, lift curves are obtained for angle-of-attack up to 40 degrees and the simulated post-stall behavior of the ilow is investigated in detail. In the active control study, both steady and synthetic jet actuators are exploited to enhance lift. Effects of parameters governing the performance of active flaw control are discussed, including blowing momentum, nondimensional actuator frequency, and jet location.