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Two Dimensional Numerical Study of Aerodynamic Characteristic for Rotating Cylinder at High Reynolds Number

Mohd Shahidi Alias(1*), A. S. Mohd Rafie(2), S. Wiriadidjaja(3)

(1) Universiti Putra Malaysia, Management and Science University, Malaysia
(2) University Putra Malaysia, Faculty of Aerospace Engineering, Malaysia
(3) Department of Aerospace Engineering, Faculty of Engineering, University Putra Malaysia, Malaysia
(*) Corresponding author


DOI: https://doi.org/10.15866/irease.v9i6.10774

Abstract


Efforts in this century for Unmanned Aerial Vehicle, UAV aerodynamic technology led to a broad of applications. Currently, UAV users are demanding of small, unprepared field or even no field for the aircraft to take off and landing operation. Aligned for the needs, several studies revealed the feasibility of rotating cylinders produced lifting which will impact the improvement of on lift coefficient. Magnus effect on rotating cylinder has the potential as a good lift generator. The studies have discovered the limitation on implementation discovered caused by induced and parasite drag occurrences. Accordingly, rotational rate, α, and Reynold number, Re, are the highlight in this study. The previous experimental and numerical data were used as a basis to compare the results. The methodological approach used for this research in order to prove the presence of Magnus effect, Finite Element Numerical Analysis method in form of 2D numerical is chosen and the simulation done by using ANSYS FLUENT R15.0 to examine the coefficient of lift, drag and understand the aerodynamic characteristics of the rotating cylinder surfaced body. Previous experimental studies carried out by Elliott G. Reid simulated on-design in 2D numerical analysis for validation. The results obtained showed 90.6% accuracy for the validation where the cylinder size to be tested was smaller compared to on-design size. The cylinder size of 30mm as adapted to J. Seifert studies on Magnus effect is used to compare the original size of 114.3mm where the Reynold number tested at the range of 1.17×103 ≤ Re ≤ 1.69×105 with rotational rate ranging from 0 ≤ α ≤ 4.32 determined by air velocity range within 5 ms-1 ≤ U ≤ 15 ms-1. Lift coefficient, CL and drag coefficient, CD determined in every stage analysis were recorded. The results obtained showed that the lift coefficient is slightly lower compared to the original size of cylinder at U are 5ms-1, 7ms-1, 10 ms-1 and 15 ms-1. However, the drag coefficient showed higher value U of 15 ms-1 and 10 ms-1 but lower at U of 5 ms-1 and 7 ms-1.


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Keywords


UAV; Magnus Effect; Rotating Cylinder; Reynolds Number; Rotational Rate; Coefficient of Lift; Coefficient of Drag; 2D Numerical Simulation

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