Non-linear calculation of the wing in general manoeuvre

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F60162694%3AG43__%2F25%3A00563881" target="_blank" >RIV/60162694:G43__/25:00563881 - isvavai.cz</a>

Výsledek na webu

<a href="https://lib.unob.cz/UNOB_CZ/FVT/K206/MDSPSL/Sborniky/MDSPSL2024_Sbornik.pdf" target="_blank" >https://lib.unob.cz/UNOB_CZ/FVT/K206/MDSPSL/Sborniky/MDSPSL2024_Sbornik.pdf</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Non-linear calculation of the wing in general manoeuvre

Popis výsledku v původním jazyce

One of the key aspects of the design process of UAVs is arguably aerodynamic analysis. This usually includes the determination of flight performance as well as stability and control characteristics in all 6 DoF. Low-fidelity methods of aerodynamic analysis are usually a satisfactory tool to perform such calculations. However, upon reviewing currently available literature, it was found out that there is currently no low-fidelity method capable of such task in sufficient depth. This paper presents a first step in developing such an algorithm. It presents a new non-linear algorithm, specifically designed to be able to calculate aerodynamic characteristics of three-dimensional wing with nonzero twist, sweep and dihedral in all 6 DoF. The results obtained with the model implemented in MATLAB are then compared with high-fidelity results for several wings, obtained with wind tunnel measurements.

Název v anglickém jazyce

Non-linear calculation of the wing in general manoeuvre

Popis výsledku anglicky

One of the key aspects of the design process of UAVs is arguably aerodynamic analysis. This usually includes the determination of flight performance as well as stability and control characteristics in all 6 DoF. Low-fidelity methods of aerodynamic analysis are usually a satisfactory tool to perform such calculations. However, upon reviewing currently available literature, it was found out that there is currently no low-fidelity method capable of such task in sufficient depth. This paper presents a first step in developing such an algorithm. It presents a new non-linear algorithm, specifically designed to be able to calculate aerodynamic characteristics of three-dimensional wing with nonzero twist, sweep and dihedral in all 6 DoF. The results obtained with the model implemented in MATLAB are then compared with high-fidelity results for several wings, obtained with wind tunnel measurements.

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<br>I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2024

Kód důvěrnosti údajů

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

Název statě ve sborníku

Sborník příspěvků 22. mezinárodní vědecké konference

ISBN

978-80-7582-515-5

ISSN

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e-ISSN

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Počet stran výsledku

20

Strana od-do

277-296

Název nakladatele

Univerzita obrany

Místo vydání

Brno

Místo konání akce

Brno

Datum konání akce

23. 10. 2024

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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