Stabilized Finite Element Approximations of Flow over a Self - Oscillating Airfoil
Result description
The paper presents the comparison of numerical solution of a 2D aeroelastic problem and experimental results. For the numerical approximation the coupled formulation of a turbulent flow over an oscillating solid airfoil is considered. The flow is modelled by the incompressible Reynolds averaged Navier-Stokes (RANS) equations rewritten in Arbitrary Lagrangian-Eulerian (ALE) form and discretized by the stabilized finite element method (FEM). The numerical results are compared with the results of optical measurements of flow field around an elastically supported vibrating double circular arc (DCA) 18% profile. The measurements were performed above the critical airflow velocity for loss of the system stability by flutter. The numerical results for the timedependent pressure distribution on the fluttering airfoil are presented.
Keywords
Arbitrary Lagrangian-Eulerian methodfinite element methodaeroelasticity
The result's identifiers
Result code in IS VaVaI
Alternative codes found
RIV/61388998:_____/10:00349276
Result on the web
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DOI - Digital Object Identifier
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Alternative languages
Result language
angličtina
Original language name
Stabilized Finite Element Approximations of Flow over a Self - Oscillating Airfoil
Original language description
The paper presents the comparison of numerical solution of a 2D aeroelastic problem and experimental results. For the numerical approximation the coupled formulation of a turbulent flow over an oscillating solid airfoil is considered. The flow is modelled by the incompressible Reynolds averaged Navier-Stokes (RANS) equations rewritten in Arbitrary Lagrangian-Eulerian (ALE) form and discretized by the stabilized finite element method (FEM). The numerical results are compared with the results of optical measurements of flow field around an elastically supported vibrating double circular arc (DCA) 18% profile. The measurements were performed above the critical airflow velocity for loss of the system stability by flutter. The numerical results for the timedependent pressure distribution on the fluttering airfoil are presented.
Czech name
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Czech description
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Classification
Type
D - Article in proceedings
CEP classification
BK - Liquid mechanics
OECD FORD branch
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Result continuities
Project
OC09019: Modelling of voice production based on biomechanics
Continuities
Z - Vyzkumny zamer (s odkazem do CEZ)
Others
Publication year
2010
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Article name in the collection
Numerical Mathematics and Advanced Applications. ENUMATH 2009
ISBN
978-3-642-11794-7
ISSN
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e-ISSN
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Number of pages
8
Pages from-to
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Publisher name
Springer
Place of publication
Berlin
Event location
Uppsala
Event date
Jun 29, 2009
Type of event by nationality
WRD - Celosvětová akce
UT code for WoS article
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Result type
D - Article in proceedings
CEP
BK - Liquid mechanics
Year of implementation
2010