Impact of Blade Trailing Edge Devices on Helicopter Rotor Aerodynamics During Hovering Flight

Abstract

The paper is dedicated to investigate the impact of the blade trailing edge device on helicopter rotor performance. The study meticulously examines the aerodynamic characteristics of various proposed models during hover flight in order to identify the optimal blade design that fulfils specific requirements. The primary objectives encompass maximizing thrust force generation while simultaneously minimizing the formation of vortices near the trailing edge. Achieving these objectives leads to the creation of a more stable system during helicopter operation. Both Computational Fluid Dynamics (CFD) and theoretical approaches were employed to conduct this research, simulating the behavior of a two-bladed rotor akin to the configuration commonly found in Bell 212 helicopters. The numerical simulations and subsequent discussions encompassed various critical aspects, including the thrust coefficient, pressure distribution, and airflow patterns. Ultimately, the investigation seeks to propose an innovative approach that enhances the overall aerodynamic performance of helicopters during hover flight.