Boundary Layer Transition, Separation and Flow Control on Airfoils, Wings and Bodies in Numerical, Wind-Tunnel and In-Flight Studies

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F11%3A00188924" target="_blank" >RIV/68407700:21220/11:00188924 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Boundary Layer Transition, Separation and Flow Control on Airfoils, Wings and Bodies in Numerical, Wind-Tunnel and In-Flight Studies

Popis výsledku v původním jazyce

Particle Image Velocimetry (PIV), smoke-wire, tuft filaments and oil-flow visualization techniques were used for wind-tunnel and in-flight investigations of boundary layer separation, both stall and separation bubbles, related to the low-Reynolds numbertransition mechanism. Airfoils of three Czech-designed sailplanes and their wing-fuselage interaction were studied. The combination of experimental results with those of numerical modeling (computational fluid dynamics, CFD) greatly facilitated the understanding of the various phenomena. The effects of several passive flow control devices, vortex generators, counter-rotating vortex generators, and zig-zag type turbulators were considered. Separation suppression was reached and corresponding drag coefficient reduction occurred for test aircraft measured in flight. Investigations were extended by the PIV time-resolved technique.

Název v anglickém jazyce

Boundary Layer Transition, Separation and Flow Control on Airfoils, Wings and Bodies in Numerical, Wind-Tunnel and In-Flight Studies

Popis výsledku anglicky

Particle Image Velocimetry (PIV), smoke-wire, tuft filaments and oil-flow visualization techniques were used for wind-tunnel and in-flight investigations of boundary layer separation, both stall and separation bubbles, related to the low-Reynolds numbertransition mechanism. Airfoils of three Czech-designed sailplanes and their wing-fuselage interaction were studied. The combination of experimental results with those of numerical modeling (computational fluid dynamics, CFD) greatly facilitated the understanding of the various phenomena. The effects of several passive flow control devices, vortex generators, counter-rotating vortex generators, and zig-zag type turbulators were considered. Separation suppression was reached and corresponding drag coefficient reduction occurred for test aircraft measured in flight. Investigations were extended by the PIV time-resolved technique.

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

<a href="/cs/project/GA101%2F08%2F1112" target="_blank" >GA101/08/1112: Řízení odtržení mezních vrstev</a><br>

Návaznosti

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

Rok uplatnění

2011

Kód důvěrnosti údajů

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

Název periodika

Technical Soaring

ISSN

0744-8996

e-ISSN

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Svazek periodika

35

Číslo periodika v rámci svazku

4

Stát vydavatele periodika

NL - Nizozemsko

Počet stran výsledku

7

Strana od-do

29-35

Kód UT WoS článku

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EID výsledku v databázi Scopus

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