Energy Efficient Active Control of the Flow Past Aircraft Wings

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F12%3APU102943" target="_blank" >RIV/00216305:26210/12:PU102943 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

čeština

Název v původním jazyce

Energy Efficient Active Control of the Flow Past Aircraft Wings

Popis výsledku v původním jazyce

Numerical simulations of the flow past a NACA 0015 wing with active control have been performed. The Reynolds number of the flow is 2.5 x 106. The configuration proposed in this study does not follow the conventional active control methodology past wings. Large blowing surfaces and low jet velocity magnitudes are considered and the energy efficiency of such configuration is examined for a number of variants. One major impact on the flow is the diffusion of the tip vortex core in the trailing edge area,but also farther downstream. Strategies for drag reduction and lift increase of the wing are proposed by varying some of the actuation parameters. The present active flow control could be efficient at all angles of attack, while in the same time could beable to reduce significantly the total drag of the wing, increase the total lift or combine effectively those favorable effects for better flight performance. Maximum drag decrease could exceed 40% of the total drag at low angles of atta

Název v anglickém jazyce

Energy Efficient Active Control of the Flow Past Aircraft Wings

Popis výsledku anglicky

Numerical simulations of the flow past a NACA 0015 wing with active control have been performed. The Reynolds number of the flow is 2.5 x 106. The configuration proposed in this study does not follow the conventional active control methodology past wings. Large blowing surfaces and low jet velocity magnitudes are considered and the energy efficiency of such configuration is examined for a number of variants. One major impact on the flow is the diffusion of the tip vortex core in the trailing edge area,but also farther downstream. Strategies for drag reduction and lift increase of the wing are proposed by varying some of the actuation parameters. The present active flow control could be efficient at all angles of attack, while in the same time could beable to reduce significantly the total drag of the wing, increase the total lift or combine effectively those favorable effects for better flight performance. Maximum drag decrease could exceed 40% of the total drag at low angles of atta

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

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Návaznosti

R - Projekt Ramcoveho programu EK

Rok uplatnění

2012

Kód důvěrnosti údajů

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

Název periodika

RESEARCH BULLETIN

ISSN

1425-2104

e-ISSN

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Svazek periodika

2012

Číslo periodika v rámci svazku

22

Stát vydavatele periodika

PL - Polská republika

Počet stran výsledku

22

Strana od-do

1-22

Kód UT WoS článku

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EID výsledku v databázi Scopus

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