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Advances in Aircraft and Spacecraft Science
  Volume 2, Number 2, April 2015 , pages 199-215
DOI: https://doi.org/10.12989/aas.2015.2.2.199
 

The effect of sweep angle on the limit cycle oscillations of aircraft wings
Seher Eken and Metin Orhan Kaya

 
Abstract
    This study focuses on the limit cycle oscillations (LCOs) of cantilever swept-back wings containing a cubic nonlinearity in an incompressible flow. The governing aeroelastic equations of two degrees-of-freedom swept wings are derived through applying the strip theory and unsteady aerodynamics. In order to apply strip theory, mode shapes of the cantilever beam are used. The harmonic balance method is used to calculate the frequencies of LCOs. Linear flutter analysis is conducted for several values of sweep angles to obtain the flutter boundaries.
 
Key Words
    limit cycle oscillations; sweep angle; harmonic balance method
 
Address
Seher Eken and Metin Orhan Kaya: Faculty of Aeronautics and Astronautics, Istanbul Technical University, Maslak Campus, 34469, Istanbul, Turkey
 

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