Cristina Riso, Amin Ghadami, Carlos E.S. Cesnik, Bogdan I. Epureanu

DOI Number: N/A

Conference number: IFASD-2019-145

Ensuring adequate flutter margins is a critical step in aircraft design. However, geometrically nonlinear configurations may develop limit cycle oscillations even before reaching the flutter boundary. When nonlinear effects are anticipated, post-flutter analyses have to be integrated into design for preventing undesirable subcritical limit cycles. Therefore, there is a need for computationally fast post-flutter analysis methods suitable for design applications. Previous work proposed an efficient method for forecasting post-flutter responses using only a few system calculations or measurements in the pre-flutter regime. This paper applies the method for investigating the post-flutter response of a practical geometrically nonlinear wing for various design choices to demonstrate the method suitability for parametric studies.

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In Categories: IFASD 2019, Limit Cycle Oscillation
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