Moveable Stagnation Point for Vortex Flow Control
Air Force Office of Scientific Research
Copper Vapor Pulsed Laser Sheet Image of the Symmetric Vortex Pattern
Over a Double Delta Winged Aircraft at 25 deg. angle of attack. GTAEAG,
1991.
A novel means of aircraft yaw and roll control during high-incidence maneuvers
has been developed. We can rapidly control the asymmetry of the vortices
generated over the forebody, and induce desired unsteady yawing and rolling
moments on an aircraft model. We have demonstrated inducement and control
of wing rock using this device, and have developed piecewise-linear transfer
functions relating nosetip motion to wind rolling moment.
Related Publications:
Darden, L.A., Magill, J.C., Komerath, N.M., AIAA Paper 95-1775, June 1995.
Darden, L.A., Peterson, K.G., Komerath, N.M., AIAA Paper 95-3468, August
'95, p. 393-403.
Peterson, K.G., Darden, L.A., Komerath, N.M., . AIAA Paper 96-0789,
January 1996.
