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farajollahi, A., niavarani, B., Rostami, M., naderi, A., bagherpour, F. (2022). Numerical Simulation and Investigation of the Effects of Vortex Generator on Aerodynamic Coefficients of the Main Helicopter Rotor in Hover. Electronic and Cyber Defense, 10(2), 55-66.
amirhamzeh farajollahi; bijan niavarani; Mohsen Rostami; ali asghar naderi; farid bagherpour. "Numerical Simulation and Investigation of the Effects of Vortex Generator on Aerodynamic Coefficients of the Main Helicopter Rotor in Hover". Electronic and Cyber Defense, 10, 2, 2022, 55-66.
farajollahi, A., niavarani, B., Rostami, M., naderi, A., bagherpour, F. (2022). 'Numerical Simulation and Investigation of the Effects of Vortex Generator on Aerodynamic Coefficients of the Main Helicopter Rotor in Hover', Electronic and Cyber Defense, 10(2), pp. 55-66.
farajollahi, A., niavarani, B., Rostami, M., naderi, A., bagherpour, F. Numerical Simulation and Investigation of the Effects of Vortex Generator on Aerodynamic Coefficients of the Main Helicopter Rotor in Hover. Electronic and Cyber Defense, 2022; 10(2): 55-66.

Numerical Simulation and Investigation of the Effects of Vortex Generator on Aerodynamic Coefficients of the Main Helicopter Rotor in Hover

مکانیک سیالات و آیرودینامیک
Article 4, Volume 10, Issue 2 - Serial Number 28, February 2022, Pages 55-66    PDF (920.39 K)
Document Type: Original Article
Authors
amirhamzeh farajollahi* 1; bijan niavarani2; Mohsen Rostami1; ali asghar naderi1; farid bagherpour3
1Assistant Professor, Imam Ali University, Tehran, Iran
2Master's student, University of Science and Technology, Tehran, Iran
3PhD student, Imam Ali University, Tehran, Iran
Receive Date: 12 September 2021,  Revise Date: 29 November 2021,  Accept Date: 10 January 2022 
Abstract
In present study, the effect of vortex generators on the aerodynamic forces of a helicopter's main rotor in hover is investigated. Vortices around blades have a significant effect on noise and aerodynamic forces. Using vortex generators is an appropriate method for decreasing the influence of flow separation and vortex around a rotor. In this study, vortex generators include four different arrangements. The numerical simulation procedure of main rotors of the helicopter blades is done by using Fluent software. The mesh grid is used in the form of unstructured. A validation with Cardona and Tang results is done. For this reason, NACA 0012 airfoil and an attack angle of 8° are used for the blades of the main rotor. It can be revealed from the results that using vortex generators, a decrease in vortex power and dimensions of transverse vortices has occurred. Also, the results show that the thrust coefficient and torque coefficient of the helicopter blades compared to the non-vortex generators mode has increased and decreased, respectively.
Keywords
Vortex generator; Numerical simulation; Aerodynamic coefficients; Hover
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