Wind tunnel measurements of flow-induced vibration of a NACA0015 airfoil model

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F14%3A00430089" target="_blank" >RIV/61388998:_____/14:00430089 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/46747885:24220/14:#0003404 RIV/46747885:24620/14:00000258

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Wind tunnel measurements of flow-induced vibration of a NACA0015 airfoil model

Popis výsledku v původním jazyce

The paper reports on interferometric measurements of flow over a NACA0015 airfoil model during flutter limit cycle oscillations. The airfoil model is fixed on an elastic support allowing motion with two degrees of freedom ? pitch and plunge. The structural mass and stiffness matrices can be tuned to certain extent, so that the eigenfrequencies of the two modes approach as needed. The model is equipped with dynamic pressure probes and sensors measuring the airfoil vertical position. The flow field aroundthe airfoil was measured by Mach-Zehnder interferometer and registered using a high-speed camera synchronously with the mechanical vibration and pressure measurements. The Mach number of the incident airflow was gradually increased and the response of the aeroelastic system to initial impulse measured, until the flutter instability onset occurred. Flutter boundaries were evaluated for various additional masses attached (i.e., for various plunging mode eigenfrequencies), and post-critica

Název v anglickém jazyce

Wind tunnel measurements of flow-induced vibration of a NACA0015 airfoil model

Popis výsledku anglicky

The paper reports on interferometric measurements of flow over a NACA0015 airfoil model during flutter limit cycle oscillations. The airfoil model is fixed on an elastic support allowing motion with two degrees of freedom ? pitch and plunge. The structural mass and stiffness matrices can be tuned to certain extent, so that the eigenfrequencies of the two modes approach as needed. The model is equipped with dynamic pressure probes and sensors measuring the airfoil vertical position. The flow field aroundthe airfoil was measured by Mach-Zehnder interferometer and registered using a high-speed camera synchronously with the mechanical vibration and pressure measurements. The Mach number of the incident airflow was gradually increased and the response of the aeroelastic system to initial impulse measured, until the flutter instability onset occurred. Flutter boundaries were evaluated for various additional masses attached (i.e., for various plunging mode eigenfrequencies), and post-critica

Druh

D - Stať ve sborníku

CEP obor

BI - Akustika a kmity

OECD FORD obor

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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

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2014

Kód důvěrnosti údajů

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

Název statě ve sborníku

Proceedings of the ASME 2014 Pressure Vessels & Piping Conference

ISBN

978-0-7918-4601-8

ISSN

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e-ISSN

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Počet stran výsledku

10

Strana od-do

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Název nakladatele

ASME

Místo vydání

Anaheim

Místo konání akce

Anaheim, California

Datum konání akce

20. 7. 2014

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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