Numerická simulace aeroelastických problémů

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F04%3A02100525" target="_blank" >RIV/68407700:21220/04:02100525 - 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 Airoelastic Problems

Popis výsledku v původním jazyce

In this paper we are interested in the interaction of two dimensional incompressible viscous laminar flow and an airfoil. For simplicity we consider only solid airfoil which can rotate and oscillate in vertical direction. The mathematical model consistsof Navier-Stokes equations written in the Arbitrary Lagrangian-Eulerian(ALE) formulation and system of ordinary differential equations describing the airfoil motion. The ALE formulation of Navier-Stokes equations is discretized by the finite element method(FEM). Nevertheless, Galerkin FEM leads to unphysical solutions if the grid is not fine enough in regions of strong gradients (e.g.boundary layer). In order to obtain physically admissible correct solutions it is neccessary to apply suitable mesh refinement combined with a stabilization technique giving stable and accurate schemes. In our paper we present SUPG stabilization method for Navier-Stokes equations. The results are compared with aerodynamical data and aeroelastic measurements

Název v anglickém jazyce

Numerical Simulation of Airoelastic Problems

Popis výsledku anglicky

In this paper we are interested in the interaction of two dimensional incompressible viscous laminar flow and an airfoil. For simplicity we consider only solid airfoil which can rotate and oscillate in vertical direction. The mathematical model consistsof Navier-Stokes equations written in the Arbitrary Lagrangian-Eulerian(ALE) formulation and system of ordinary differential equations describing the airfoil motion. The ALE formulation of Navier-Stokes equations is discretized by the finite element method(FEM). Nevertheless, Galerkin FEM leads to unphysical solutions if the grid is not fine enough in regions of strong gradients (e.g.boundary layer). In order to obtain physically admissible correct solutions it is neccessary to apply suitable mesh refinement combined with a stabilization technique giving stable and accurate schemes. In our paper we present SUPG stabilization method for Navier-Stokes equations. The results are compared with aerodynamical data and aeroelastic measurements

Druh

A - Audiovizuální tvorba

CEP obor

BA - Obecná matematika

OECD FORD obor

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Projekt

<a href="/cs/project/GA101%2F02%2F0391" target="_blank" >GA101/02/0391: Numerická simulace a experimentální výzkum aeroelasticity leteckých konstrukcí s uvážením velkých výchylek</a><br>

Návaznosti

Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2004

Kód důvěrnosti údajů

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

ISBN

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Místo vydání

Patras

Název nakladatele resp. objednatele

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Verze

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