Experimental and Numerical Investigation of Post-Flutter Limit Cycle Oscillations on a Cantilevered Flat Plate

Ramesh, K. , Monteiro, T. P., Silvestre, F. J., Antonio Bernardo, G. N., Siqueira Versiani, T. d. S. and Gil Annes da Silva, R. (2017) Experimental and Numerical Investigation of Post-Flutter Limit Cycle Oscillations on a Cantilevered Flat Plate. International Forum on Aeroelasticity and Structural Dynamics 2017, Como, Italy, 25-28 Jun 2017.

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Abstract

Futuristic aircraft designs and novel aircraft such as High Altitude Long Endurance (HALE) involve a higher level of structural flexibility than in conventional aircraft. Even at present, the trends in the aviation industry are to increase wing length (to reduce induced drag) and maxi- mize use of composites, which lead to increased structural flexibility. This necessitates a rethink of conventional (linear) aeroelastic analysis, since the increased flexibility results in coupling between the flight dynamic and aeroelastic dynamics, and consequently, limit-cycle oscillations of the structure. In this paper, a new three-dimensional low-order model for unsteady aerody- namics that accounts for large oscillation amplitudes and nonplanar wakes is developed. An experiment with a cantilevered flat plate at low Reynolds number is set up and used to validate the low-order model, as well as to study post-flutter limit-cycle oscillations. Results from the low-order model are promising, but show that aerodynamic nonlinearities such as flow sepa- ration and leading-edge vortex shedding must also be modeled in order to predict all possible limit-cycle oscillations of the aeroelastic system.

Item Type:Conference or Workshop Item
Status:Published
Refereed:No
Glasgow Author(s) Enlighten ID:Ramesh, Dr Kiran
Authors: Ramesh, K., Monteiro, T. P., Silvestre, F. J., Antonio Bernardo, G. N., Siqueira Versiani, T. d. S., and Gil Annes da Silva, R.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Copyright Holders:Copyright © 2017 The Authors
Publisher Policy:Reproduced with the permission of the Authors

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Project CodeAward NoProject NamePrincipal InvestigatorFunder's NameFunder RefLead Dept
725041Development of a Fast Computational Tool for Highly Flexible Flight DynamicsKiran RameshRoyal Academy of Engineering (RAE)NRCP1516/4/26ENG - AEROSPACE SCIENCES