High-fidelity static aeroelastic simulations of the common research model
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F20%3APU136674" target="_blank" >RIV/00216305:26210/20:PU136674 - isvavai.cz</a>
Result on the web
<a href="https://www.scopus.com/record/display.uri?eid=2-s2.0-85083454609&origin=resultslist&sort=plf-f&src=s&st1=978-3-030-36514-1&st2=&sid=410e5c752d9acf21e5b37834ade9d822&sot=b&sdt=b&sl=22&s=ALL%28978-3-030-36514-1%29&relpos=7&citeCnt=0&searchTerm=" target="_blank" >https://www.scopus.com/record/display.uri?eid=2-s2.0-85083454609&origin=resultslist&sort=plf-f&src=s&st1=978-3-030-36514-1&st2=&sid=410e5c752d9acf21e5b37834ade9d822&sot=b&sdt=b&sl=22&s=ALL%28978-3-030-36514-1%29&relpos=7&citeCnt=0&searchTerm=</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1007/978-3-030-36514-1_4" target="_blank" >10.1007/978-3-030-36514-1_4</a>
Alternative languages
Result language
angličtina
Original language name
High-fidelity static aeroelastic simulations of the common research model
Original language description
Current aircraft design leads to increased flexibility of the airframe as a result of modern materials application or aerodynamically efficient slender wings. The airframe flexibility influences the aerodynamic performance and it might significantly impact the aeroelastic effects, which can be more easily excited by rigid body motions than in case of stiffer structures. The potential aeroelastic phenomena can occur in large range of speeds involving transonic regime, where the non-linear flow effects significantly influence the flutter speed. Common aeroelastic analysis tools are mostly based on the linear theories for aerodynamic predictions, thus they fail to predict mentioned non-linear effect. This paper presents the first step in the design of high-fidelity aeroelastic simulation tool. Currently, it allows to perform static aeroelastic simulations by coupling Computational Fluid Dynamics solver with Matlab based Finite Element solver. The structural solver is a linear elasticity solver which is able to solve either models consisting of beam elements or arbitrary models using stiffness and mass matrices exported from Nastran solver. The aeroelastic interface is based on the Radial Basic Functions. The test case studied in this work is a static aeroelastic simulation of the Common Research Model in the transonic conditions. The structural models tested are a wing-box finite element model and a beam stick model which is statically equivalent to the wing-box model. The comparison of results using respective structural models shows good agreement in aerodynamic properties of the model wing at static equilibrium state.
Czech name
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Czech description
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Classification
Type
D - Article in proceedings
CEP classification
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OECD FORD branch
20304 - Aerospace engineering
Result continuities
Project
<a href="/en/project/LO1202" target="_blank" >LO1202: NETME CENTRE PLUS</a><br>
Continuities
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)
Others
Publication year
2020
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Article name in the collection
Flexible Engineering Toward Green Aircraft
ISBN
978-3-030-36514-1
ISSN
1613-7736
e-ISSN
1860-0816
Number of pages
22
Pages from-to
49-70
Publisher name
Springer
Place of publication
Neuveden
Event location
Řím
Event date
Dec 14, 2017
Type of event by nationality
EUR - Evropská akce
UT code for WoS article
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