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

Seher Eken; Metin Orhan Kaya

doi:10.12989/aas.2015.2.2.199

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

Seher Eken^*, Metin Orhan Kaya

^*Corresponding author for this work

Research output: Contribution to journal › Article › peer-review

3 Citations (Scopus)

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.

Original language	English
Pages (from-to)	199-215
Number of pages	17
Journal	Advances in Aircraft and Spacecraft Science
Volume	2
Issue number	2
DOIs	https://doi.org/10.12989/aas.2015.2.2.199
Publication status	Published - 1 Apr 2015

Bibliographical note

Publisher Copyright:
© 2015 Techno-Press, Ltd.

Keywords

Harmonic balance method
limit cycle oscillations
Sweep angle

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10.12989/aas.2015.2.2.199

Cite this

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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.",

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

Abstract

Bibliographical note

Keywords

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