SUMMARY

Flight control by distributed fluidic modification of the apparent aerodynamic shape of a an airfoil is investigated experimentally. Control is effected by the interaction of integrated arrays of fluidic actuators with the cross flow by leveraging the generation and regulation (trapping) of vorticity concentrations near the surface to alter its aerodynamic shape and thereby the aerodynamic forces and moments. This flow control approach is investigated in a series of wind tunnel tests of the dynamic response of a free-moving airfoil model to commanded 2-DOF maneuvers (pitch and plunge). Bi-directional changes in the pitching moment over a range of angles of attack are effected by nominally-symmetric trapped vorticity concentrations on both the suction and pressure surfaces near the trailing edge using hybrid actuators. Flow control effectiveness is demonstrated by closed-loop response to a momentary force disturbance which is analogous to the response to a sudden gust in free flight.