A hybrid boundary element based aeroelastic model for flexible wing.

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F20%3A00535617" target="_blank" >RIV/61388998:_____/20:00535617 - isvavai.cz</a>

Result on the web

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DOI - Digital Object Identifier

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Result language

angličtina

Original language name

A hybrid boundary element based aeroelastic model for flexible wing.

Original language description

The paper describes development of medium delity aeroelastic numerical model for fast aeroelastic analysis of the flexible aeronautical structures e.g. wings, rotor blades etc. The numerical model is developed particularly for the incompressible low subsonic flow regime application. For the flow field modeling boundary element based hybrid panel method flow solver with viscous-inviscid coupling strategy have been successfully developed and implemented here.The unsteady flow field is modeled using hybrid/modi ed panel method where, integral boundary layer theory (vis-cous part), surface panel method (potential flow inviscid part) and vortex particle method (separated shear layer modeling) are coupled together. The proposed model can simulate both attached and separated flow fields. The estimated aerodynamic lift coefficients and the pressure coefficient are compared with experimental results for static and dynamic stall flow conditions. Furthermore, the results from new aeroelastic model will be compared with classical CFD-CSD based aeroelastic models for efficiency and accuracy check. The proposed methodology for the aeroelastic analysis of long exible aeronautical structure will provide researchers and engineers a fast, cost effective and efficient tool for aeroelastic analysis for different design at preliminary design stage where large numbers of design iteration are required within short time frame.

Czech name

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Czech description

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Type

D - Article in proceedings

CEP classification

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OECD FORD branch

20302 - Applied mechanics

Project

<a href="/en/project/GA20-26779S" target="_blank" >GA20-26779S: Study of dynamic stall flutter instabilities and their consequences in turbomachinery application by mathematical, numerical and experimental methods</a><br>

Continuities

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year

2020

Confidentiality

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

Article name in the collection

Dymamesi 2020

ISBN

978-80-87012-73-4

ISSN

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e-ISSN

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Number of pages

6

Pages from-to

39-44

Publisher name

Institute of Thermomechanics Academy of Sciences of the Czech Republic, v. v. i.

Place of publication

Praha

Event location

Praha

Event date

Mar 3, 2020

Type of event by nationality

EUR - Evropská akce

UT code for WoS article

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