Active Control of Separation from the Flap of a Supercritical Airfoil

Active flow control in the form of periodic zero-mass-flux excitation was applied at several regions on the leading edge and trailing edge flaps of a simplified high-lift system t o delay flow separation.The NASA Energy Efficient Transport (EET) supercritical airfoil was equipped with a 15% chord simply hinged leading edge flap and a 25% chord simply hinged trailing edge flap.Detailed flow features were measured in an attempt to identify optimal actuator placement.The measurements included steady and unsteady model and tunnel wall pressures, wake surveys, arrays of surface hot-films, flow visualization, and particle image velocimetry (PIV).The current paper describes the application of active separation control a t several locations on the deflected trailing edge flap.High frequency (F+ Y 10) and low frequency amplitude modulation ( F i A I FZ 1) of the high frequency excitation were used for control.Preliminary efforts to combine leading and trailing edge flap excitations are also reported.Nomenclature model chord oscillatory excitation nioineiit urnpressure coefficient oscillation frequency, Hz reduced frequency, = (f xsp)/UlIlf slot height or width oscillatory moineiitum at slot exit, hlach number pressure static pressure freestream dyiianiic pressure, 1 /2pUm2 chord Reyiiolds number, EE U,c/v distance from actuator to trailing edge temperature average and fluctuating streamwise velocity uormalized streamwise location phui