Experimental Simulation of Flapping Wings for Nano-Air-Vehicles

摘要

This paper presents recent progress in a continuing investigation of the aeromechanical aspects of generation of aerodynamic forces of flapping wings. A tailored experimental facility is developed for flapping wings operating at high reduced frequency with a complex two-dimensional or three-dimensional pattern. The experimental measurements are demonstrated by the test cases of two-dimensional and three-dimensional flapping wings, designed according to the proposed notional nano-air-vehicle at a hovering condition. The features of the water tunnel, the geometric and kinematic parameters of the airfoils/wings, and the setups of the motion rigs for each test case are described in detail. The measured forces and particle image velocimetry data are analyzed and cross-checked with the numerical results obtained from an in-house code. The analyses and comparisons of the experimental and numerical results confirm that the established experimental approach obtained a quantitatively reliable solution for the development of flapping wings and can serve for numerical validation. This is an essential step towards engineering realization of the functionality of insect flight.