Advances in aircraft and spacecraft science

  • 제2권2호
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  • Pages.199-215
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  • 2015
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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The effect of sweep angle on the limit cycle oscillations of aircraft wings

  • Eken, Seher (Faculty of Aeronautics and Astronautics, Istanbul Technical University) ;
  • Kaya, Metin Orhan (Faculty of Aeronautics and Astronautics, Istanbul Technical University)
  • 투고 : 2014.05.20
  • 심사 : 2014.12.20
  • 발행 : 2015.04.25
⟨ 이전 논문 다음 논문 ⟩

초록

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.

키워드

참고문헌

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피인용 문헌

  1. Effect of sweep angle on bifurcation analysis of a wing containing cubic nonlinearity vol.3, pp.4, 2016, https://doi.org/10.12989/aas.2016.3.4.447
  2. Design optimization of a fixed wing aircraft vol.4, pp.1, 2017, https://doi.org/10.12989/aas.2017.4.1.065