Volume 2 - Issue 2, March - April 2026

Blade twist is an important geometric parameter affecting the aerodynamic performance of helicopter rotors in hover. Due to the radial variation of tangential velocity along the blade span, rotors with constant pitch angles tend to produce non-uniform aerodynamic loading and reduced efficiency. This study investigates the influence of blade twist on the hover efficiency of a helicopter main rotor using a parametric aerodynamic analysis. The results show that blade twist improves the spanwise distribution of aerodynamic loads and significantly enhances rotor efficiency. The results provide useful guidance for the aerodynamic design and optimization of helicopter rotor blades.

Huu Dung Nguyen, Trong Thuong Tran, Van Tuyen Nguyen,"Effect of Blade Twist on the Hover Efficiency of a Helicopter Main Rotor" International Journal of Advanced Multidisciplinary Research and Educational Development, V2(2): Page(1206-1208) Mar-Apr 2026. ISSN: 3107-6513. www.ijamred.com. Published by Scientific and Academic Research Publishing.