Experiments performed on a low-speed Circulation-Controlled Airfoil are described. The airfoil was of elliptic section with the circulation controlled by means of a jet blowing around the blunt trailing edge and rotating the cylindrical trailing edge.
The purpose of this study is to investigate the effects of rotation of trailing edge on lift.
Results for the lift, drag and pitching moment on the airfoil are presented as functions of the angle of incidence, the blowing momentum coefficient and the tangential velocity of rotating cylinder.
Experiments were performed in the range 0.009≤$C\mu$≤0.074 at Re $= 2.8(10^5)$.
Lift increases with $C\mu$, however, it decreases with increasing slot-height at constant $C\mu$. This decrease in lift can be increased by trailing edge rotation.
