CFD Analysis of Flapping Wing for MICAV Application

Abstract

CFD analysis of flapping wing is required for the design of MICAV configuration. The basic aerodynamic phenomenon for MICAV flapping wing flight is unsteady flow, spiraling leading edge vortex formation which is responsible for sustained flight at low speeds, wake capturing which adds additional lift, and fast pitch up which generates positive lift at the time of stroke reversal. In this paper, an investigation has been done for a typical MICAV flapping wing configuration. Wing is subjected to sinusoidal flapping oscillations with a frequency 25 Hz, amplitude of 45° up-stroke, and 35° down-stroke; span of the wing, 45 cm; chord, 15 cm; thickness is varied from 0.025 to 0.1 mm; leading edge is straight and trailing edge is curved. CFD unsteady solution is obtained and analyzed. It has been found that 0.025 mm thick wing tends to generate more lift and thrust than 0.1 mm thick wing.