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

Eken S., Kaya M. O.

ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE, vol.2, no.2, pp.199-215, 2015 (ESCI) identifier identifier

  • Publication Type: Article / Article
  • Volume: 2 Issue: 2
  • Publication Date: 2015
  • Doi Number: 10.12989/aas.2015.2.2.199
  • Journal Name: ADVANCES IN AIRCRAFT AND SPACECRAFT SCIENCE
  • Journal Indexes: Emerging Sources Citation Index (ESCI), Scopus
  • Page Numbers: pp.199-215
  • Keywords: limit cycle oscillations, sweep angle, harmonic balance method, NONLINEAR AEROELASTIC ANALYSIS, HOMOTOPY ANALYSIS METHOD, INCOMPRESSIBLE-FLOW, RESTORING FORCES, AIRFOIL MOTION, FLUTTER, BIFURCATION
  • Istanbul Technical University Affiliated: Yes

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.