Numerical Investigation of Variation Stroke Plane Effect on Aerodynamic Performance of a 2D Flapping Airfoil Naca 0012 in Hovering Fligh

Abstract

This paper presents a numerical study of the effects generated by the variation of translation plane inclination angle on the aerodynamic performance (aerodynamic forces, energy consumption, and wing flow structures). This inclination angle is called ? (such as 90° ? ? ? 0°). In our work, a two-dimensional NACA0012 airfoil will be presented using Ansys Fluent commercial software based on the finite volumes method (FVM).The numerical simulations are carried out using the experimental results parameters. Symmetric wing flapping motions with different angles of the stroke plane inclination ? in conjunction with other kinematic parameters such as oscillation amplitude (15° ? ?? ? 45°) and Reynolds number (1.35. 105 ? ???? ? 1.35) are examined to investigate the influence of these parameters on the energy consumption of the NACA0012 profile. The governing parameters of the problem under study are: the chord of the profile C, the initial angle of rotation ?0 , the oscillation amplitude ??, the reduced frequency k, Reynolds number ???? = 1.35 × 105, flow velocity U? , turbulence intensity at the inlet is 0.08%, translation amplitude Am and phase difference between the rotation and translation motion ? .The obtained numerical results were compared with the experimental data. Moreover, vorticity and pressure contours for different values of angle ? will be also presented