Parallel Numerical Simulation of Oscillating Airfoil Naca0015 in the Channel Due to Flutter Instability

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F46747885%3A24220%2F14%3A%230003389" target="_blank" >RIV/46747885:24220/14:#0003389 - isvavai.cz</a>

Výsledek na webu

<a href="http://dx.doi.org/10.1051/epjconf/20146702098" target="_blank" >http://dx.doi.org/10.1051/epjconf/20146702098</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1051/epjconf/20146702098" target="_blank" >10.1051/epjconf/20146702098</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Parallel Numerical Simulation of Oscillating Airfoil Naca0015 in the Channel Due to Flutter Instability

Popis výsledku v původním jazyce

The work is devoted to 3D and 2D parallel numerical computation of pressure and velocity fields around an elastically supported airfoil self-oscillating due to interaction with the airflow. Numerical solution is computed in the OpenFOAM package, an open-source software package based on finite volume method. Movement of airfoil is described by translation and rotation, identified from experimental data. A new boundary condition for the 2DOF motion of the airfoil was implemented. The results of numericalsimulations (velocity) are compared with data measured in a wind tunnel, where a physical model of NACA0015 airfoil was mounted and tuned to exhibit the flutter instability. The experimental results were obtained previously in the Institute of Thermomechanics by interferographic measurements in a subsonic wind tunnel in Nový Knín

Název v anglickém jazyce

Parallel Numerical Simulation of Oscillating Airfoil Naca0015 in the Channel Due to Flutter Instability

Popis výsledku anglicky

The work is devoted to 3D and 2D parallel numerical computation of pressure and velocity fields around an elastically supported airfoil self-oscillating due to interaction with the airflow. Numerical solution is computed in the OpenFOAM package, an open-source software package based on finite volume method. Movement of airfoil is described by translation and rotation, identified from experimental data. A new boundary condition for the 2DOF motion of the airfoil was implemented. The results of numericalsimulations (velocity) are compared with data measured in a wind tunnel, where a physical model of NACA0015 airfoil was mounted and tuned to exhibit the flutter instability. The experimental results were obtained previously in the Institute of Thermomechanics by interferographic measurements in a subsonic wind tunnel in Nový Knín

Druh

D - Stať ve sborníku

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

—

Projekt

<a href="/cs/project/GA13-10527S" target="_blank" >GA13-10527S: Analýza subsonického flutteru elasticky uložených profilů s využitím interferometrie a CFD</a><br>

Návaznosti

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

Rok uplatnění

2014

Kód důvěrnosti údajů

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

Název statě ve sborníku

EPJ Web of Conferences

ISBN

—

ISSN

2100-014X

e-ISSN

—

Počet stran výsledku

4

Strana od-do

1-4

Název nakladatele

EDP Sciences

Místo vydání

Les Ulis, Francie

Místo konání akce

Kutná Hora

Datum konání akce

1. 1. 2013

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

000343672100101