The vortex structure shed from the trailing-dege of a constant-rate pitching airfoil was visualized using hydrogen bubble technique.

The problem of unsteady separated flow of rapidly pitching airfoil with oscillating motion is computationally studied.

Experiments of flow visualization and dynamic unsteady pressure measurement with pitching-up delta wings are carried out in a water channel and a wind tunnel,respectively in order to study the flow and frequency characteristics of the leading-edge vortices over a delta wing undergoing pitching up-stop motions.

Experimental investigation on unsteady aerodynamics of rotor-blade airfoil;