Abstract—Currently, multirotor Unmanned Aerial Vehicles (UAVs) typically use propellers rotating around a vertical axis. However, the cyclorotor is a type of multirotor that the propellers rotate around the lateral axis. This configuration offers advantages such as increased compactness, stiffness, and safety compared to conventional rotors. This article focuses on studying the aerodynamic behavior of cyclorotors. The objective of this article is to study the effect of pitch angle amplitudes on the lift, propulsive force, torque, and lift-todrag ratio using 2D Computational Fluid Dynamics (CFD) simulation. The variables of this study were as follows: the pitch angle amplitudes of 25º, 35º, 45º and the rotor speeds consisted of 400, 500, 600, 700, and 800 RPM. As a result, (i) The pitch angle amplitude of 45 degrees provided the highest lift of 29.717 N at 800 RPM. (ii) The pitch angle amplitude of 45º produced the maximum propulsive force of 11.026 N at 800 RPM. (iii) The pitch angle amplitude of 25º offered the lowest torque of 0.239 N.m at 400 RPM. (iv) The pitch angle amplitude of 25º s promoted the highest lift-to-torque ratio of 12.705 at 800 RPM.

Keywords—cyclorotor, computational fluid dynamics, unmanned aerial vehicle

Cite: Wishchayapas Piluck, Kitsada Sangnak, Anaswee Arbubaka, and Teerawat Klabklay, "The Effect of Pitch Angle Amplitudes on a Cyclorotor Performance Using Computational Fluid Dynamics," International Journal of Mechanical Engineering and Robotics Research, Vol. 14, No. 5, pp. 471-479, 2025. doi: 10.18178/ijmerr.14.5.471-479

Copyright © 2025 by the authors. This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).