Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design

Abstract The flapping rotary wing as a novel layout of micro air vehicle (MAV) remains being tested. Boring-hole design was applied to decrease the negative lift generated in wing's upstroke motion. The lift of traditional and boring-hole wingwere measured, contrasted and analyzed by experiments. Another series of experiments was conducted to explore the effect of the hinge material. It is indicated that a critical angle of attack ( α t ) exist to confirm the lift increment of the perforated wing, and the maximum increment can be up to 35% of the maximummean lift.