H. R. Hamdani - Aerospace Engineering Department, College of Aeronautical Engineering, National University of Sciences and Technology, Pakistan
A. Aizaz - Aerospace Engineering Department, College of Aeronautical Engineering, National University of Sciences and Technology, Pakistan
M. A. Naqvi - Aerospace Engineering Department, College of Aeronautical Engineering, National University of Sciences and Technology, Pakistan

The aerodynamic force and the flow structure of a wing performing hovering motion at small Reynolds number (Re=۴۰۰۰) is calculated by computationally solving the ۳D Navier-Stokes equations. The computations are performed for the hovering motion which consists of stroke ۱, followed by the flipping motion for reversing the direction and then the stroke ۲ (similar to stroke ۱ but in the opposite direction). The intent of the study is to research the effects of different scheduling of the flip motion between the two strokes. At Re=۴۰۰۰, the delayed stall mechanism is noted during the azimuth rotation of a wing with a high value of CL due to stabilized Leading Edge Vortex. The lift contribution during the flip (pitch rotation for reversing the direction) for the complete stroke is not substantial. During a stroke, the wing encountered the wake from the previous stroke in which, the wake does not contribute positively.

Hovering, Delayed stall, Low Reynolds number, Wake capture, Flip scheduling, CFD