Numerical and experimental modelling of transition in a separated boundary layer on the NACA63A421 Airfiol

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F10%3A00359604" target="_blank" >RIV/61388998:_____/10:00359604 - 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

Numerical and experimental modelling of transition in a separated boundary layer on the NACA63A421 Airfiol

Popis výsledku v původním jazyce

The paper is concerned with numerical modelling of transition of separated boundary layer. The model of laminar/turbulent transition is based on the combination of empirical terms determining position of the transition and averaged Navier-Stokes equations closed by the k-? SST turbulence model. The model of transition is applied in computation of 2D flow past NACA63A421 airfoil. Computation is performed using the commercial code ANSYS Fluent 6.3.26, in which the transition method is implemented as a User-Defined-Function. Computed distributions of Cp along the airfoil are verified by comparison with experimental data, which were obtained by measurements in a closed circuit wind tunnel at the constant Reynolds number and several angles of attack. Comparisons prove applicability of the implemented trasitional model.

Název v anglickém jazyce

Numerical and experimental modelling of transition in a separated boundary layer on the NACA63A421 Airfiol

Popis výsledku anglicky

The paper is concerned with numerical modelling of transition of separated boundary layer. The model of laminar/turbulent transition is based on the combination of empirical terms determining position of the transition and averaged Navier-Stokes equations closed by the k-? SST turbulence model. The model of transition is applied in computation of 2D flow past NACA63A421 airfoil. Computation is performed using the commercial code ANSYS Fluent 6.3.26, in which the transition method is implemented as a User-Defined-Function. Computed distributions of Cp along the airfoil are verified by comparison with experimental data, which were obtained by measurements in a closed circuit wind tunnel at the constant Reynolds number and several angles of attack. Comparisons prove applicability of the implemented trasitional model.

Druh

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

CEP obor

BK - Mechanika tekutin

OECD FORD obor

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Projekt

Výsledek vznikl pri realizaci vícero projektů. Více informací v záložce Projekty.

Návaznosti

Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2010

Kód důvěrnosti údajů

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

Název periodika

Sborník vědeckých prací Vysoké školy báňské - Technické univerzity Ostrava

ISSN

1210-0471

e-ISSN

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Svazek periodika

56

Číslo periodika v rámci svazku

3

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

7

Strana od-do

47-53

Kód UT WoS článku

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EID výsledku v databázi Scopus

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