EFFECT OF VORTEX GENERATORS ON FLOW CONDITIONS OF AIRFOIL WITH DEFLECTED FLAP

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F10%3A00351475" target="_blank" >RIV/61388998:_____/10:00351475 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/68407700:21220/10:00181070

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

EFFECT OF VORTEX GENERATORS ON FLOW CONDITIONS OF AIRFOIL WITH DEFLECTED FLAP

Popis výsledku v původním jazyce

This paper focuses on a suppression of the flow separation, which occurs on a deflected flap, by means of vortex generators (VGs). An airfoil NACA 63A421 with a simple flap and vane-type vortex generators were used. The investigation was carried out by using experimental and numerical methods. The data from the numerical simulation of the flapped airfoil without VGs control were used for the vortex generator design. Two sizes, two different shapes and various spacing of the vortex generators were tested. The flow past the airfoil was visualized through two methods, namely tuft filaments technique and oil visualization. The experiments were performed in closed circuit wind tunnels with closed and open test sections. The lift curves for both cases with and without vortex generators were acquired for the determination of the lift coefficient improvement. The improvement was achieved for several cases by means all of the applied methods.

Název v anglickém jazyce

EFFECT OF VORTEX GENERATORS ON FLOW CONDITIONS OF AIRFOIL WITH DEFLECTED FLAP

Popis výsledku anglicky

This paper focuses on a suppression of the flow separation, which occurs on a deflected flap, by means of vortex generators (VGs). An airfoil NACA 63A421 with a simple flap and vane-type vortex generators were used. The investigation was carried out by using experimental and numerical methods. The data from the numerical simulation of the flapped airfoil without VGs control were used for the vortex generator design. Two sizes, two different shapes and various spacing of the vortex generators were tested. The flow past the airfoil was visualized through two methods, namely tuft filaments technique and oil visualization. The experiments were performed in closed circuit wind tunnels with closed and open test sections. The lift curves for both cases with and without vortex generators were acquired for the determination of the lift coefficient improvement. The improvement was achieved for several cases by means all of the applied methods.

Druh

D - Stať ve sborníku

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

Výsledek vznikl pri realizaci vícero projektů. Více informací v záložce Projekty.

Návaznosti

Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2010

Kód důvěrnosti údajů

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

Název statě ve sborníku

21st International Symposium on Transport Phenomena

ISBN

978-986-6184-25-3

ISSN

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e-ISSN

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Počet stran výsledku

8

Strana od-do

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Název nakladatele

National Kaohsiung University of Applied Sciences

Místo vydání

Kaohsiung City

Místo konání akce

Kaohsiung City

Datum konání akce

2. 11. 2010

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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