Verification and possible applications of new 3D panel method with boundary layer

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F17%3A00319377" target="_blank" >RIV/68407700:21220/17:00319377 - isvavai.cz</a>

Výsledek na webu

<a href="http://stc.fs.cvut.cz/history/2017/sbornik/papers/pdf/6577.pdf?_=1491843908" target="_blank" >http://stc.fs.cvut.cz/history/2017/sbornik/papers/pdf/6577.pdf?_=1491843908</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Verification and possible applications of new 3D panel method with boundary layer

Popis výsledku v původním jazyce

Robust and well tested 3D panel method for potential flow solution was coupled to a two-equation integral 2D boundary layer model. The result is a sophisticated tool for solving the problem of both steady and unsteady viscous flow around streamlined lifting bodies such as wings or blades of turbomachines in external flow. The key aspect of the model is a quasi-simultaneous computation using interaction coefficients that allow solution of boundary layer with transition and other regions of strong interaction. The advantages and shortcomings of the new model are discussed based on the comparison with CFD results and the results of an advanced lifting line model. An elliptic wing with NACA4415 airfoil was chosen as a test case for comparison. Drag evaluation in the Trefftz plane was used as an alternative method for drag calculation in order to minimize force over surface integration error.

Název v anglickém jazyce

Verification and possible applications of new 3D panel method with boundary layer

Popis výsledku anglicky

Robust and well tested 3D panel method for potential flow solution was coupled to a two-equation integral 2D boundary layer model. The result is a sophisticated tool for solving the problem of both steady and unsteady viscous flow around streamlined lifting bodies such as wings or blades of turbomachines in external flow. The key aspect of the model is a quasi-simultaneous computation using interaction coefficients that allow solution of boundary layer with transition and other regions of strong interaction. The advantages and shortcomings of the new model are discussed based on the comparison with CFD results and the results of an advanced lifting line model. An elliptic wing with NACA4415 airfoil was chosen as a test case for comparison. Drag evaluation in the Trefftz plane was used as an alternative method for drag calculation in order to minimize force over surface integration error.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

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Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2017

Kód důvěrnosti údajů

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

Název statě ve sborníku

Studentská tvůrčí činnost 2017 - sborník konference

ISBN

978-80-01-06143-5

ISSN

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e-ISSN

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Počet stran výsledku

10

Strana od-do

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Název nakladatele

ČVUT v Praze - Fakulta strojní

Místo vydání

Praha

Místo konání akce

Praha

Datum konání akce

20. 4. 2017

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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