This research paper aims to investigate the optimization of smaller propeller blades to achieve maximum efficiency by studying the effect of the twist angle on reducing drag, increasing thrust, and preventing rapid wear on the blade. Inefficient propellers consume a significant amount of energy, particularly during low-speed flights. The low Reynolds number regime challenges aviation engineers to design propellers with the highest possible efficiency to minimize energy losses. The primary objective of this thesis is to optimize smaller propeller blade shapes to enable them to produce maximum efficiency. The advanced ratio of a propeller blade heavily influences the blade's performance efficiency. The analysis uses the modified Blade Element Momentum Theory (BEM) and the Betz optimization method, with an analytical approach for comparing methods. The results show that the aerodynamic twist angle plays a vital role in propeller blade performance in a low Reynolds number regime. An optimized twist angle can improve efficiency up to eight times, as per the preliminary data, highlighting the critical role of optimization in achieving maximum efficiency in propeller blades.
Bachelor Science in Aerospace Engineering (B.S.A.E.)
College of Engineering and Computer Science
Mechanical and Aerospace Engineering
Nabid, Fahad M., "An Optimization Study of Small-Scale Propeller Blade" (2023). Honors Undergraduate Theses. 1393.