DESIGN OPTIMIZATION OF COMPOSITE PROPELLER BLADES FOR LIGHTWEIGHT AIRCRAFT

Abstract

This investigation's primary goal is to improve the aerodynamic efficiency, structural integrity, and overall performance of composite propeller blades for light aircraft, all while minimizing their weight and fuel consumption. This study investigates the possible uses of modern composite materials, especially carbon fiber reinforced polymers, because of their exceptional strength, corrosion resistance, and longer lifespan after repeated usage. Computer programs and modeling tools are used to assess the blade's chord distribution, twist angle, airfoil shape, and fiber orientation in order to maximize performance in a range of working circumstances. The distribution of stress, vibration, power production, and airflow of propeller blades are examined using computational fluid dynamics (CFD) and finite element analysis (FEA). The improved composite blade design weighs less during manufacturing, has less structural deformation, lasts longer, and is more effective than conventional metal blades. This makes it perfect for the lightweight aircraft applications of today.