Computational fluid dynamics simulation on aerodynamic characteristics of ONERA M6-wing

Abstract

According to the Global Aviation Development, The Unmanned Aerial Vehicles plays a vital role in leading the aviation industry. Designing an unmanned aerial vehicle with low Reynolds number and long endurance are the challenging task to achieve efficient flight. This investigation concentrated on the wing performance parameters that are influences the stability of solar power unmanned aerial vehicles. In general solar powered unmanned aerial vehicles can be operated in low altitude with very minimum velocity. Supporting to improve the flying qualities of solar powered unmanned aerial vehicles, ONERA M6 wing designed and validated in aerodynamic aspects. In this present work solar powered unmanned aerial vehicle is designed to be operated in the transonic region with swept wing configuration and often adhering to the phenomenon of Whitcomb Area rule. Satisfying the conditions of flight profile, the boundaries are far-field 3-dimensional, transonic, turbulent, and in viscid, flow simulations over the ONERA M6 wing about the respective angle of attack. Computational Fluid Dynamics Results have been validated for various flow conditions and which are best suits for operating the solar powered unmanned aerial vehicle in transonic region. Observation from the results and an optimization can be made in the autonomous wing body for conventional operation.