Investigation of Limit Cycle Oscillations of Transport Aircraft
Vignesh S1, Naveen R2, Sajath Kumar3, Lakshmanan D4, Vadivelu P5
1Vignesh S, Independent Researcher, Department of Aeronautical, Bannari Amman Institute of Technology, Erode (Tamil Nadu), India.
2Naveen R, Department of Aeronautical, Bannari Amman Institute of Technology, Erode (Tamil Nadu), India.
3Sajath Kumar, Scientist D, ADA, Bangalore (Karnataka), India.
4Lakshmanan D, Department of Aeronautical, Bannari Amman Institute of Technology, Erode (Tamil Nadu), India.
5Vadivelu P, Department of Aeronautical, Bannari Amman Institute of Technology, Erode (Tamil Nadu), India.
Manuscript received on 13 December 2018 | Revised Manuscript received on 22 December 2018 | Manuscript Published on 30 December 2018 | PP: 134-138 | Volume-8 Issue-2S, December 2018 | Retrieval Number: 100.1/ijeat.B10361282S18/18©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The Limit Cycle Oscillations (LCO) produced at the time of cruising flight segment is a serious concern in the large airplanes. The three dimensional fully coupled FluidStructural Interaction (FSI) analysis on a swept back wing with control surface is a challenge due to many uncertainties. To measure nonlinear aeroelastic phenomena like LCO caused by fluid-structure interaction in transonic range, Computational Fluid Dynamics (CFD)/ Computational Structure Dynamics (CSD) coupled simulations is proposed. It reveals the specific properties of the wing with control surface modal and allows the investigation of unstable behavior using experimental or numerical solution at transonic flow conditions. The simulation is done using Reynolds Averaged Navier Stokes (RANS) equations coupled with Spalart–Allmaras one- equation turbulence model. The obtained LCO frequency, amplitudes, mean lift and moment values are used to analyze the nonlinear aerodynamic effects. The solutions are reliant on the initial fields or perturbation. The LCO with very small amplitudes are determined by the developed (CFD)/ (CSD) simulation. This is endorsed to the fully coupled FSI turbulence model of higher order low diffusion schemes.
Keywords: Aeroelasticity, Limit Cycle Oscillation, Uncertainties, Coupled FSI Analysis, Frequency Response, Nonlinear Aerodynamics, CFD/CSD, Navier-Stokes Equations, Transonic Region, Simple Design Framework Methodology.
Scope of the Article: Transportation Engineering