Energy Efficient Active Control of the Flow Past Aircraft Wings

Result code in 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>

Result on the web

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DOI - Digital Object Identifier

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Result language

čeština

Original language name

Energy Efficient Active Control of the Flow Past Aircraft Wings

Original language description

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

Czech name

Energy Efficient Active Control of the Flow Past Aircraft Wings

Czech description

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

Type

J_x - Unclassified - Peer-reviewed scientific article (Jimp, Jsc and Jost)

CEP classification

JU - Aeronautics, aerodynamics, aeroplanes

OECD FORD branch

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Project

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Continuities

R - Projekt Ramcoveho programu EK

Publication year

2012

Confidentiality

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

Name of the periodical

RESEARCH BULLETIN

ISSN

1425-2104

e-ISSN

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Volume of the periodical

2012

Issue of the periodical within the volume

22

Country of publishing house

PL - POLAND

Number of pages

22

Pages from-to

1-22

UT code for WoS article

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EID of the result in the Scopus database

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