Abstract
Linear and non-linear aeroelastic analyses of swept cantilever wings containing a cubic non-linearity in an incompressible flow are investigated. Expressions of aerodynamic forces and moments for an element of the swept wing are derived in the time domain using a relation between Theodorsen and Wagner's functions. Consequently, the governing aeroelastic equations of two degrees of freedom wings are derived for both swept backward and forward wings. Linear analysis is carried out via solving the governing equations with the standard fourth-order Runge—Kutta method. For the sake of verification of the derived formulas, the results of the numerical solution for a linear flutter boundary are compared with the experimental data in several cases. Considering softening and hardening cubic structural non-linearities, non-linear analysis of the swept wing is studied. For the wings containing hardening cubic non-linearities, the first- and third-order harmonic balance (HB) methods are employed to find the amplitude and frequency of limit cycle oscillations (LCOs). Comparison between results of the HB method and those of the numerical solution of the governing equations indicates a close agreement. Finally, few parameters on the linear and non-linear flutter boundaries and also the amplitude and frequency of the LCO are studied.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
More From: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.