Improvement of Computational Results of NASA Airliner Model by Wing Modal Analysis

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F17%3AN0000039" target="_blank" >RIV/00010669:_____/17:N0000039 - isvavai.cz</a>

Výsledek na webu

<a href="https://arc.aiaa.org/doi/pdf/10.2514/1.C033952" target="_blank" >https://arc.aiaa.org/doi/pdf/10.2514/1.C033952</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.2514/1.C033952" target="_blank" >10.2514/1.C033952</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Improvement of Computational Results of NASA Airliner Model by Wing Modal Analysis

Popis výsledku v původním jazyce

The NASA Common Research Model of an airliner was used for the evaluation of the effect of aeroelasticity on aerodynamic forces and local flowfield. A computational fluid dynamics analysis of the rigid model showed large differences between the computational and experimental data. It was observed that the model (in particular, the wing) deformation has a significant effect on the aerodynamic characteristics. Online mesh deformation on the basis of wing modal analysis was used to improve the accuracy of the computational results. Twenty modes in total were used during coupled simulations. The results from these simulations showed that adding the wing deformation into the computational fluid dynamics simulation improved the accuracy of obtained aerodynamic coefficients. The same methodology was applied to the full-model configuration considering the deformation of all parts of the model. The results from the computational fluid dynamics analyses with online mesh deformation of the semispan and full model are the focus of this paper.

Název v anglickém jazyce

Improvement of Computational Results of NASA Airliner Model by Wing Modal Analysis

Popis výsledku anglicky

The NASA Common Research Model of an airliner was used for the evaluation of the effect of aeroelasticity on aerodynamic forces and local flowfield. A computational fluid dynamics analysis of the rigid model showed large differences between the computational and experimental data. It was observed that the model (in particular, the wing) deformation has a significant effect on the aerodynamic characteristics. Online mesh deformation on the basis of wing modal analysis was used to improve the accuracy of the computational results. Twenty modes in total were used during coupled simulations. The results from these simulations showed that adding the wing deformation into the computational fluid dynamics simulation improved the accuracy of obtained aerodynamic coefficients. The same methodology was applied to the full-model configuration considering the deformation of all parts of the model. The results from the computational fluid dynamics analyses with online mesh deformation of the semispan and full model are the focus of this paper.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/7E13056" target="_blank" >7E13056: 2nd Generation Active Wing – Active Flow- Loads & Noise control on next generation wing</a><br>

Návaznosti

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

Rok uplatnění

2017

Kód důvěrnosti údajů

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

Název periodika

Journal of Aircraft

ISSN

0021-8669

e-ISSN

1533-3868

Svazek periodika

54

Číslo periodika v rámci svazku

4

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

9

Strana od-do

1294-1302

Kód UT WoS článku

000406240300005

EID výsledku v databázi Scopus

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