Numerical Analysis of Helicopter Rotor at 400 Rpm
K.M. Pandey1, A. Surana2, D. Deka3
1Dr. K M Pandey, is currently working as Professor, Department of Mechanical Engineering, NIT Silchar, Assam, India.
2A. Surana, is 8th semester, B.Tech , Mechanical Engineering student at National Institute of Technology Silchar, Silchar, India.
3D. Deka, is 8th semester, B.Tech Mechanical Engineering student at National Institute of Technology Silchar, Silchar, India.
Manuscript received on February 15, 2012. | Revised Manuscript received on February 20, 2012. | Manuscript published on March 05, 2012. | PP: 253-258 | Volume-2 Issue-1, March 2012. | Retrieval Number: A0428022112 /2012©BEIESP
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© The Authors. Published By: 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: In this paper the main objective of this simulation is to analyze the flow around an isolated main helicopter rotor at a particular main rotor speed of 400 rpm, and angle of attack of 8 degrees and blades of the helicopter Eurocopter AS350B3 which uses the blade profile of standard ONERA OA209 airfoil during hovering flight conditions. For CFD analysis, the Motion Reference Frame (MRF) method with standard viscous k-ε turbulent flow model was used on modeling the rotating rotor operating in hovering flight. The Ansys fluent was used for the purpose of analysis.
Keywords: Aerodynamics, CFD, helicopter, hovering, MRF, rpm.