Aerodynamic modelling of a tilt-wing transition corridor

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F22%3AN0000071" target="_blank" >RIV/00010669:_____/22:N0000071 - isvavai.cz</a>

Výsledek na webu

<a href="https://iopscience.iop.org/journal/1742-6596" target="_blank" >https://iopscience.iop.org/journal/1742-6596</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Aerodynamic modelling of a tilt-wing transition corridor

Popis výsledku v původním jazyce

With the recent rapid evolution of the UAM class concepts in past years, the re-emerged interest in VTOL concepts and their aerodynamics arises. The tilt-wing is one of the possible solutions for such a vehicle. Recent decades of tilt-wing aerodynamic research point to the importance of the understanding transition regime from cruise to hover. Especially the wing stall phenomena which affect descent capabilities and control during the landing phase. Understanding such a regime is crucial for optimal wing design. This paper presents several approaches to the modelling of aerodynamic forces during the critical phase of transition. Computations are aimed particularly to the edge of the flight envelope. The low to high fidelity methods are employed and compared with the results of low-speed wind tunnel testing. The results from high fidelity methods match well with experimental results but the proposed simple analytical model fails in prediction of the transition corridor in the most critical regimes.

Název v anglickém jazyce

Aerodynamic modelling of a tilt-wing transition corridor

Popis výsledku anglicky

With the recent rapid evolution of the UAM class concepts in past years, the re-emerged interest in VTOL concepts and their aerodynamics arises. The tilt-wing is one of the possible solutions for such a vehicle. Recent decades of tilt-wing aerodynamic research point to the importance of the understanding transition regime from cruise to hover. Especially the wing stall phenomena which affect descent capabilities and control during the landing phase. Understanding such a regime is crucial for optimal wing design. This paper presents several approaches to the modelling of aerodynamic forces during the critical phase of transition. Computations are aimed particularly to the edge of the flight envelope. The low to high fidelity methods are employed and compared with the results of low-speed wind tunnel testing. The results from high fidelity methods match well with experimental results but the proposed simple analytical model fails in prediction of the transition corridor in the most critical regimes.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

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Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2022

Kód důvěrnosti údajů

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

Název statě ve sborníku

Journal of Physics: Conference Series

ISBN

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ISSN

1742-6596

e-ISSN

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Počet stran výsledku

7

Strana od-do

nestrankovano

Název nakladatele

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Místo vydání

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Místo konání akce

Barcelona

Datum konání akce

18. 10. 2022

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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