Using wing model deformation for improvement of CFD results of ESWIRP project

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F18%3AN0000031" target="_blank" >RIV/00010669:_____/18:N0000031 - isvavai.cz</a>

Výsledek na webu

<a href="https://link.springer.com/article/10.1007/s13272-018-0286-3" target="_blank" >https://link.springer.com/article/10.1007/s13272-018-0286-3</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1007/s13272-018-0286-3" target="_blank" >10.1007/s13272-018-0286-3</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Using wing model deformation for improvement of CFD results of ESWIRP project

Popis výsledku v původním jazyce

The NASA Common Research Model has been used for evaluation of the effect of the deformation of the model on aerodynamic forces and local flowfield. Large differences were observed during comparison of the results of the rigid model and experimental data obtained during ESWIRP project at European Transonic Windtunnel. On-line mesh deformation using 20 modes in total was used during coupled CFD simulations to improve the accuracy of the numerical results. The results from these simulations showed that adding the wing deformation into the computational fluid dynamics simulation improved the accuracy of obtained aerodynamic coefficients and also the local flowfield. The results from the coupled CFD simulation with on-line mesh deformation of the semispan model are the focus of this paper.

Název v anglickém jazyce

Using wing model deformation for improvement of CFD results of ESWIRP project

Popis výsledku anglicky

The NASA Common Research Model has been used for evaluation of the effect of the deformation of the model on aerodynamic forces and local flowfield. Large differences were observed during comparison of the results of the rigid model and experimental data obtained during ESWIRP project at European Transonic Windtunnel. On-line mesh deformation using 20 modes in total was used during coupled CFD simulations to improve the accuracy of the numerical results. The results from these simulations showed that adding the wing deformation into the computational fluid dynamics simulation improved the accuracy of obtained aerodynamic coefficients and also the local flowfield. The results from the coupled CFD simulation with on-line mesh deformation of the semispan model are the focus of this paper.

Druh

J_SC - Článek v periodiku v databázi SCOPUS

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2018

Kód důvěrnosti údajů

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

Název periodika

CEAS Aeronautical Journal

ISSN

1869-5582

e-ISSN

1869-5590

Svazek periodika

9

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

CH - Švýcarská konfederace

Počet stran výsledku

12

Strana od-do

361–372

Kód UT WoS článku

—

EID výsledku v databázi Scopus

2-s2.0-85047568631