The effect of sweep angle on the limit cycle oscillations of aircraft wings


Eken S., Kaya M. O.

ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE, cilt.2, ss.199-215, 2015 (ESCI İndekslerine Giren Dergi) identifier identifier

  • Cilt numarası: 2 Konu: 2
  • Basım Tarihi: 2015
  • Doi Numarası: 10.12989/aas.2015.2.2.199
  • Dergi Adı: ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE
  • Sayfa Sayıları: ss.199-215

Özet

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.