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Volume 7, Number 1, January 2022 , pages 69-79 DOI: https://doi.org/10.12989/acd.2022.7.1.069 |
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An analytical approach for aeroelastic analysis of tail flutter |
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Amin Gharaei, Hamid Rabieyan-Najafabadi, Hossein Nejatbakhsh and Ahmad Reza Ghasemi
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| Abstract | ||
| In this research, the aeroelastic instability of a tail section manufactured from aluminum isotropic material with different shell thickness investigated. For this purpose, the two degrees of freedom flutter analytical approach are used, which is accompanied with simulation by finite element analysis. Using finite element analysis, the geometry parameters such as the center of mass, the aerodynamic center and the shear center are determined. Also, by simulation of finite element method, the bending and torsional stiffnesses for various thickness of the airfoil section are determined. Furthermore, using Lagrange's methods the equations of motion are derived and modal frequency and critical torsional/bending modes are discussed. The results show that with increasing the thickness of the isotropic airfoil section, the flutter and divergence speeds increased. Compared of the obtained results with other research, indicates a good agreement and reliability of this method. | ||
| Key Words | ||
| aeroelastic instability; aluminum airfoil section; finite element analysis; flutter speed | ||
| Address | ||
| Amin Gharaei: Faculty of Engineering, Yazd University, Yazd, Iran Hamid Rabieyan-Najafabadi: Faculty of New Sciences and Technologies, University of Tehran, Tehran, Iran Hossein Nejatbakhsh: Faculty of Mechanical Engineering, University of Kashan, Kashan, Iran Ahmad Reza Ghasemi: Faculty of Mechanical Engineering, University of Kashan, Kashan, Iran | ||
