Dynamic Experiments At High Angle Of Attack And Plasma Flow Control On Forebody

When the aircraft is at large Angle of attack, asymmetric flow appears on the head and accompany occurrence large lateral force. In the first part of this paper , there are kinds of plane model ,one is routine layout, the other is canard layout. Through the large amplitude pitch dynamic test at high angle large of attack in the wind tunnel, the lateral-directional unsteady aerodynamics of two models are compared. The influence of canard wind at ateral-directional unsteady aerodynamics is studied. When the forebody strake is applied at the nose tip of routine model, the force and moment are suppressed effectively at the high angles of attack, not only the static test but also the dynamic test. So the lateral-directional aerodynamic characteristics are improved.Then, the induced velocity fields of three plasma actuators, H-type ,L -type and O-type, are measured quantitatively by using the PIV in quiescent air. The flow field structures are analyzed. The effects of the geometric structure and excitation voltage are studied. It was found that L-type actuators induce a sloping jet which direction is along the top angle bisection, O-type and H-type produce vertical jet, jet velocity increases with the increase of excitation voltage. The velocity of the jet inducted by H-type actuator is influenced by the width between electrodes. The direction of the jet inducted by L-type actuator is influenced by the angle of the electrode. The velocity of the jet inducted by O-type actuator is influenced by the diameter of the electrode.In the last part , the regular plasma actuators and l-type actuators are respectively applied at the nose tip of a new spin adult. We try to control the head asymmetric vortex at large Angle of attack by using these actuator. The results show that, by opening the side of the actuator, the direction of asymmetric vortex can be changed.