Computational mesh and rans model of turbulence sensitivity in CFD optimization of slotted flap

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F16%3APU124427" target="_blank" >RIV/00216305:26210/16:PU124427 - 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

Computational mesh and rans model of turbulence sensitivity in CFD optimization of slotted flap

Popis výsledku v původním jazyce

As powerful and relatively fast and cheap tools, CFD solvers are used for solution of wide range of problems in the aerodynamics including the search for optimal position of slotted flap. If relative difference between CFD result and real behavior of the flow varies strongly with the flap configuration, predicted optimum may vary from the real one as well. Therefore a test case focused on estimation of this type of error was conducted. This article presents results of computed 2D aerodynamic of NACA 66(2)-216 airfoil with 25% slotted flap deployed and located at 25 different positions. Combination of unstructured and hybrid computational meshes with total number of elements ranging from 79 to 330 thousands and three RANS models of turbulence were applied. For each model of turbulence a consistency of results with respect to the mesh density is discussed in the article and compared to the general recommendations. Finally, the data obtained from CFD solution were validated against the wind tunnel measur

Název v anglickém jazyce

Computational mesh and rans model of turbulence sensitivity in CFD optimization of slotted flap

Popis výsledku anglicky

As powerful and relatively fast and cheap tools, CFD solvers are used for solution of wide range of problems in the aerodynamics including the search for optimal position of slotted flap. If relative difference between CFD result and real behavior of the flow varies strongly with the flap configuration, predicted optimum may vary from the real one as well. Therefore a test case focused on estimation of this type of error was conducted. This article presents results of computed 2D aerodynamic of NACA 66(2)-216 airfoil with 25% slotted flap deployed and located at 25 different positions. Combination of unstructured and hybrid computational meshes with total number of elements ranging from 79 to 330 thousands and three RANS models of turbulence were applied. For each model of turbulence a consistency of results with respect to the mesh density is discussed in the article and compared to the general recommendations. Finally, the data obtained from CFD solution were validated against the wind tunnel measur

Druh

O - Ostatní výsledky

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/LO1202" target="_blank" >LO1202: NETME CENTRE PLUS</a><br>

Návaznosti

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

Rok uplatnění

2016

Kód důvěrnosti údajů

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