Numerical Simulation of Influence of a Gap between the Main Lifting Surface and the Aileron on Aeroelastic Behaviour of an Airfoil

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F12%3A00198420" target="_blank" >RIV/68407700:21220/12:00198420 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Numerical Simulation of Influence of a Gap between the Main Lifting Surface and the Aileron on Aeroelastic Behaviour of an Airfoil

Popis výsledku v původním jazyce

The contribution deals with numerical simulations of the interaction of two-dimensional (2D) incompressible viscous flow and a vibrating airfoil NACA 0012. The flexibly supported airfoil with three degrees of freedom (3 - DOF) is performing rotation around the elastic axis, oscillations in the vertical direction and rotation of the aileron around the axis. The finite element (FE) solution of the Navier - Stokes equations is strongly coupled with a system of nonlinear ordinary differential equations describing the airfoil motion with large amplitudes. The time-dependent computational domain and a moving grid are treated by the Arbitrary Lagrangian-Eulerian (ALE) method. The developed method is used in the theoretical prediction of the aerodynamic damping, limit cycle oscillations (LCO) and the flutter instability of the airfoil, especially concerning the effects of the geometry and the size of the gap between the main lifting surface and the aileron.

Název v anglickém jazyce

Numerical Simulation of Influence of a Gap between the Main Lifting Surface and the Aileron on Aeroelastic Behaviour of an Airfoil

Popis výsledku anglicky

The contribution deals with numerical simulations of the interaction of two-dimensional (2D) incompressible viscous flow and a vibrating airfoil NACA 0012. The flexibly supported airfoil with three degrees of freedom (3 - DOF) is performing rotation around the elastic axis, oscillations in the vertical direction and rotation of the aileron around the axis. The finite element (FE) solution of the Navier - Stokes equations is strongly coupled with a system of nonlinear ordinary differential equations describing the airfoil motion with large amplitudes. The time-dependent computational domain and a moving grid are treated by the Arbitrary Lagrangian-Eulerian (ALE) method. The developed method is used in the theoretical prediction of the aerodynamic damping, limit cycle oscillations (LCO) and the flutter instability of the airfoil, especially concerning the effects of the geometry and the size of the gap between the main lifting surface and the aileron.

Druh

D - Stať ve sborníku

CEP obor

BI - Akustika a kmity

OECD FORD obor

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Projekt

<a href="/cs/project/GAP101%2F11%2F0207" target="_blank" >GAP101/11/0207: Sdružené úlohy mechaniky tekutin a těles - nelineární aeroelasticita</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2012

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

Flow - Induced Vibrations

ISBN

978-0-9548583-4-6

ISSN

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e-ISSN

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Počet stran výsledku

8

Strana od-do

147-154

Název nakladatele

School of Engineering, Trinity College

Místo vydání

Dublin

Místo konání akce

Dublin

Datum konání akce

2. 7. 2012

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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