Visualization of boundary layer separation and passive flow control on airfoils and bodies in wind-tunnel and in-flight experiments
Identifikátory výsledku
Kód výsledku v IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F12%3A00379086" target="_blank" >RIV/61388998:_____/12:00379086 - isvavai.cz</a>
Výsledek na webu
<a href="http://dx.doi.org/10.1051/epjconf/20122501078" target="_blank" >http://dx.doi.org/10.1051/epjconf/20122501078</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1051/epjconf/20122501078" target="_blank" >10.1051/epjconf/20122501078</a>
Alternativní jazyky
Jazyk výsledku
angličtina
Název v původním jazyce
Visualization of boundary layer separation and passive flow control on airfoils and bodies in wind-tunnel and in-flight experiments
Popis výsledku v původním jazyce
Infrared camera, Particle Image Velocimetry, smoke-wire, tuft filaments and oil-flow visualization techniques were used for wind-tunnel and in-flight investigation of boundary layer separation, both stall and separation bubbles, related to the low-Reynolds numbers transition mechanism. Airfoils of Wortmann FX66 series and FX66 series wing-fuselage interaction, as well as modern airfoils and their wing-fuselage geometry were subject to study. The presence of previously identified structures in the CFD modelling, such as horse-shoe vortices, was confirmed in the flow. Wind-tunnels and in-flight measurements on sailplanes were carried out and effect of passive flow control devices - vortex generators - was surveyed; namely counter-rotating vortex generators and Zig-zag type turbulators were applied. Separation suppression and consequent drag coefficient reduction of test aircrafts was reached. PIV investigation was further extended by Time-Resolved techniques. An important study on struct
Název v anglickém jazyce
Visualization of boundary layer separation and passive flow control on airfoils and bodies in wind-tunnel and in-flight experiments
Popis výsledku anglicky
Infrared camera, Particle Image Velocimetry, smoke-wire, tuft filaments and oil-flow visualization techniques were used for wind-tunnel and in-flight investigation of boundary layer separation, both stall and separation bubbles, related to the low-Reynolds numbers transition mechanism. Airfoils of Wortmann FX66 series and FX66 series wing-fuselage interaction, as well as modern airfoils and their wing-fuselage geometry were subject to study. The presence of previously identified structures in the CFD modelling, such as horse-shoe vortices, was confirmed in the flow. Wind-tunnels and in-flight measurements on sailplanes were carried out and effect of passive flow control devices - vortex generators - was surveyed; namely counter-rotating vortex generators and Zig-zag type turbulators were applied. Separation suppression and consequent drag coefficient reduction of test aircrafts was reached. PIV investigation was further extended by Time-Resolved techniques. An important study on struct
Klasifikace
Druh
D - Stať ve sborníku
CEP obor
BK - Mechanika tekutin
OECD FORD obor
—
Návaznosti výsledku
Projekt
<a href="/cs/project/GA101%2F08%2F1112" target="_blank" >GA101/08/1112: Řízení odtržení mezních vrstev</a><br>
Návaznosti
Z - Vyzkumny zamer (s odkazem do CEZ)<br>I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace
Ostatní
Rok uplatnění
2012
Kód důvěrnosti údajů
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Údaje specifické pro druh výsledku
Název statě ve sborníku
EFM11 - EXPERIMENTAL FLUID MECHANICS 2011
ISBN
—
ISSN
2100-014X
e-ISSN
—
Počet stran výsledku
12
Strana od-do
—
Název nakladatele
E D P SCIENCES
Místo vydání
HOGGAR
Místo konání akce
Jičín
Datum konání akce
22. 11. 2011
Typ akce podle státní příslušnosti
WRD - Celosvětová akce
Kód UT WoS článku
000304449600078