Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings

Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings

A method is presented to model the incompressible, attached, unsteady lift and pitching moment acting on a thin three-dimensional wing in the time domain. The model is based on the combination of Wagner theory and lifting line theory through the unsteady Kutta–Joukowski theorem. The result...

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Bibliographic Details
Main Authors: Johan Boutet, Grigorios Dimitriadis
Format: Article
Language:English
Published: MDPI AG 2018-09-01
Series:Aerospace
Subjects:
unsteady aerodynamics
finite wings
Wagner theory
lifting line theory
aeroelasticity
Online Access:http://www.mdpi.com/2226-4310/5/3/92
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spelling doaj-77d6bbd01c054d7eada0fda9cb368b012020-11-25T01:48:51ZengMDPI AGAerospace2226-43102018-09-01539210.3390/aerospace5030092aerospace5030092Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D WingsJohan Boutet0Grigorios Dimitriadis1Aerospace and Mechanical Engineering Department, University of Liège, Quartier Polytech 1, Allée de la découverte, 9, 4000 Liège, Belgium.Aerospace and Mechanical Engineering Department, University of Liège, Quartier Polytech 1, Allée de la découverte, 9, 4000 Liège, Belgium.A method is presented to model the incompressible, attached, unsteady lift and pitching moment acting on a thin three-dimensional wing in the time domain. The model is based on the combination of Wagner theory and lifting line theory through the unsteady Kutta–Joukowski theorem. The results are a set of closed-form linear ordinary differential equations that can be solved analytically or using a Runge–Kutta–Fehlberg algorithm. The method is validated against numerical predictions from an unsteady vortex lattice method for rectangular and tapered wings undergoing step or oscillatory changes in plunge or pitch. Further validation is demonstrated on an aeroelastic test case of a rigid rectangular finite wing with pitch and plunge degrees of freedom.http://www.mdpi.com/2226-4310/5/3/92unsteady aerodynamicsfinite wingsWagner theorylifting line theoryaeroelasticity
collection DOAJ
language English
format Article
sources DOAJ
author Johan Boutet
Grigorios Dimitriadis
spellingShingle Johan Boutet
Grigorios Dimitriadis
Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
Aerospace
unsteady aerodynamics
finite wings
Wagner theory
lifting line theory
aeroelasticity
author_facet Johan Boutet
Grigorios Dimitriadis
author_sort Johan Boutet
title Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
title_short Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
title_full Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
title_fullStr Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
title_full_unstemmed Unsteady Lifting Line Theory Using the Wagner Function for the Aerodynamic and Aeroelastic Modeling of 3D Wings
title_sort unsteady lifting line theory using the wagner function for the aerodynamic and aeroelastic modeling of 3d wings
publisher MDPI AG
series Aerospace
issn 2226-4310
publishDate 2018-09-01
description A method is presented to model the incompressible, attached, unsteady lift and pitching moment acting on a thin three-dimensional wing in the time domain. The model is based on the combination of Wagner theory and lifting line theory through the unsteady Kutta–Joukowski theorem. The results are a set of closed-form linear ordinary differential equations that can be solved analytically or using a Runge–Kutta–Fehlberg algorithm. The method is validated against numerical predictions from an unsteady vortex lattice method for rectangular and tapered wings undergoing step or oscillatory changes in plunge or pitch. Further validation is demonstrated on an aeroelastic test case of a rigid rectangular finite wing with pitch and plunge degrees of freedom.
topic unsteady aerodynamics
finite wings
Wagner theory
lifting line theory
aeroelasticity
url http://www.mdpi.com/2226-4310/5/3/92
work_keys_str_mv AT johanboutet unsteadyliftinglinetheoryusingthewagnerfunctionfortheaerodynamicandaeroelasticmodelingof3dwings
AT grigoriosdimitriadis unsteadyliftinglinetheoryusingthewagnerfunctionfortheaerodynamicandaeroelasticmodelingof3dwings
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