Research of Noise in the Unmanned Aerial Vehicle’s Propeller using CFD
Vijayanandh R1, Ramesh M2, Raj Kumar G3, Thianesh U K4, Venkatesan K5, Senthil Kumar M6
1Vijayanandh R, Assistant Professor, Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore (Tamil Nadu), India.
2Ramesh M, BE Student, Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore (Tamil Nadu), India.
3Raj Kumar G, Assistant Professor, Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore (Tamil Nadu), India.
4Thianesh U K, BE Student, Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore (Tamil Nadu), India.
5Venkatesan K, ME Student, Department of Mechanical Engineering, Alagappa Chettiar Government College of Engineering and Technology, Karaikudi (Tamil Nadu), India.
6Senthil Kumar M, Assistant Professor (SRG), Department of Aeronautical Engineering, Kumaraguru College of Technology, Coimbatore (Tamil Nadu), India.
Manuscript received on 15 August 2019 | Revised Manuscript received on 27 August 2019 | Manuscript Published on 06 September 2019 | PP: 145-150 | Volume-8 Issue- 6S, August 2019 | Retrieval Number: F10310886S19/19©BEIESP | DOI: 10.35940/ijeat.F1031.0886S19
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The major use and need of the multi-rotor UAV in various fields has increased the importance to study the aerodynamics of multi-rotor Unmanned Aerial Vehicles such as the secondary flow over the blade, reduction of noise due to the propeller of the UAV, and the optimization of the design on the propeller with more blades to increase efficiency of the UAV. This paper mainly deals with the reduction of noise which is induced by the propeller. Since there is a demand for compact multi-rotor quite UAV as it has a low probability of detection using radar and infrared but as it generates high drive-line noise caused by propeller it cannot be implemented for some critical applications. As a result, an idea is launched to design a propeller with low drive-line noise levels. A methodology is developed to design a low noise as well as efficient propellers for multi-rotor UAVs. The important parameters like blade thickness, tip loss and blade loading are considered in this research. Also, the effects of propeller important parameters such as activity factor, advance ratio are considered. After the finalization of design consideration of UAV’s propeller and the furthermore noise reduction methodologies also studied such as leading-edge comb, trailing edge tuft, and upper surface porosity in order to generate a perfect UAV for military applications. In order to minimize the noise produced by the propeller the idea of modifying the leading-edges is finalized. Computer-AidedDesign of base propeller and propeller with leading-edge modifications has been generated with the help of CATIA V5 and the acoustic analysis for the static base and propellers with leading-edge modifications with different velocities has been simulated using ANSYS Workbench Fluent 16.2. Finally, a propeller with the leading-edge modification has been found to induce low noise.
Keywords: Noise, CFD, Decibel, Propeller, Quite UAV.
Scope of the Article: Operational Research