A three degree-of-freedom aeroelastic typical section with control surface freeplay is modeled theoretically as a system of piecewise linear state-space models . The system response is determined by time marching of the governing equations using a standard Runge -Kutta algorithm in conjunction with
Analysis of limit cycle oscillations of a typical airfoil section with freeplay
โ Scribed by Zhang, Si-Jin; Wen, Gui-Lin; Peng, Fan; Liu, Zi-Qiang
- Book ID
- 120999462
- Publisher
- The Chinese Society of Theoretical and Applied Mechanics; Institute of Mechanics, Chinese Academy of Sciences
- Year
- 2013
- Tongue
- English
- Weight
- 552 KB
- Volume
- 29
- Category
- Article
- ISSN
- 0567-7718
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A two-dimensional flexible airfoil with a freeplay non-linearity in pitch has been analyzed in the subsonic flow range. Structurally, the airfoil is modelled as finite beam elements and two spring elemens in pitch and plunge. A doublet lattice method is used for the two-dimensional unsteady aerodyna
A three-degree-of-freedom aeroelastic model with freeplay is modeled theoretically using a small number of aerodynamic eigenmodes (i.e. a reduced order model) based upon Peters' finite-state model for two-dimensional aerodynamic flow. The limit cycle behavior and the sensitivity to initial condition