Piezo-stack vortex generators for boundary layer control of a delta wing micro-aerial vehicle

• The piezo-stack vortex generators for boundary layer control in a delta wing micro-aerial vehicle (MAV) are proposed.
• The design and specification of the vortex piezo-generators are presented.
• The MAV flow control conception by using vortex piezo-generators is investigated.
• The model of the vortex piezo-generator control system is developed.
• Wind tunnel measurements are performed and results are discussed.

This paper presents an idea for the control of flow separation over solid surfaces by piezo-stack vortex generators. The vortex generators are small vibrating plates attached to the delta wing surface. A model of the micro-aerial vehicle (MAV) controlled by vortex piezo-generators is presented. The vortex generators are applied to produce the appropriate aerodynamical forces and moments controlling the flight of the aircraft. The efficiency of the vortex generators is proved by the wind tunnel test results. The oscillatory added lift and drag coefficients versus angle of attack are presented. The optimal vortex generator amplitude and frequency are investigated. Boundary layer control (BLC) for delta wing micro-aircraft increases the manoeuvrability and performance of the MAV.