Progress in Control Actuators for Dynamic Stall Alleviation. G.U. Aero Report 9919

Summary: This paper reports on a continuing investigation into trailing edge actuators for use in dynamic stall alleviation. A discrete vortex code is used to model the flow over a NACA 0015 section as it pitches from 0 to 40 degrees at pitch rates from 0.0266 to 0.0974. Various static actuators have been modelled, including a blunted trailing edge, notches of varying depths, and trailing edge flaps. These experiments show that static actuators do not have enough of an affect on the flow over the airfoil to provide an effective solution. This investigation will therefore continue by investigating the use of dynamically moving actuators.