Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction

Xiangying Chen, GeCheng Zha, Ming Ta Yang

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Citations (Scopus)

Abstract

This paper describes a numerical methodology coupling Navier-Stokes equations and structural modal equations for predicating 3D transonic wing flutter. A dual-time step implicit unfactored Gauss-Seidel iteration with Roe scheme are employed for the flow solver. A modal approach is used for the structural response. The flow and structural solvers are fully coupled vis successive iterations within each physical time step. The accuracy of the modal approach structure solver is validated with finite element solver ANSYS. The results indicate that the first five modes are sufficient to accurately model the wing structure response for present study. The computed flutter boundary of AGARD wing 445.6 for free stream Mach numbers ranging from 0.499 to 1.141 agrees well with the experiment.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Pages8340-8356
Number of pages17
Volume11
StatePublished - Dec 1 2006
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
Duration: Jan 9 2006Jan 12 2006

Other

Other44th AIAA Aerospace Sciences Meeting 2006
CountryUnited States
CityReno, NV
Period1/9/061/12/06

Fingerprint

flutter
Flutter (aerodynamics)
wings
iteration
Fluids
fluid
fluids
Computer simulation
simulation
structural response
transonic flow
free flow
Navier-Stokes equations
interactions
Mach number
Navier-Stokes equation
Navier Stokes equations
methodology
experiment
Experiments

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Chen, X., Zha, G., & Yang, M. T. (2006). Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting (Vol. 11, pp. 8340-8356)

Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction. / Chen, Xiangying; Zha, GeCheng; Yang, Ming Ta.

Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 11 2006. p. 8340-8356.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Chen, X, Zha, G & Yang, MT 2006, Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction. in Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. vol. 11, pp. 8340-8356, 44th AIAA Aerospace Sciences Meeting 2006, Reno, NV, United States, 1/9/06.
Chen X, Zha G, Yang MT. Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 11. 2006. p. 8340-8356
Chen, Xiangying ; Zha, GeCheng ; Yang, Ming Ta. / Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 11 2006. pp. 8340-8356
@inproceedings{f8efced241394f86bc15f9cfa6937935,
title = "Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction",
abstract = "This paper describes a numerical methodology coupling Navier-Stokes equations and structural modal equations for predicating 3D transonic wing flutter. A dual-time step implicit unfactored Gauss-Seidel iteration with Roe scheme are employed for the flow solver. A modal approach is used for the structural response. The flow and structural solvers are fully coupled vis successive iterations within each physical time step. The accuracy of the modal approach structure solver is validated with finite element solver ANSYS. The results indicate that the first five modes are sufficient to accurately model the wing structure response for present study. The computed flutter boundary of AGARD wing 445.6 for free stream Mach numbers ranging from 0.499 to 1.141 agrees well with the experiment.",
author = "Xiangying Chen and GeCheng Zha and Yang, {Ming Ta}",
year = "2006",
month = "12",
day = "1",
language = "English",
isbn = "1563478072",
volume = "11",
pages = "8340--8356",
booktitle = "Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting",

}

TY - GEN

T1 - Numerical simulation of 3-D wing flutter with fully coupled fluid-structural interaction

AU - Chen, Xiangying

AU - Zha, GeCheng

AU - Yang, Ming Ta

PY - 2006/12/1

Y1 - 2006/12/1

N2 - This paper describes a numerical methodology coupling Navier-Stokes equations and structural modal equations for predicating 3D transonic wing flutter. A dual-time step implicit unfactored Gauss-Seidel iteration with Roe scheme are employed for the flow solver. A modal approach is used for the structural response. The flow and structural solvers are fully coupled vis successive iterations within each physical time step. The accuracy of the modal approach structure solver is validated with finite element solver ANSYS. The results indicate that the first five modes are sufficient to accurately model the wing structure response for present study. The computed flutter boundary of AGARD wing 445.6 for free stream Mach numbers ranging from 0.499 to 1.141 agrees well with the experiment.

AB - This paper describes a numerical methodology coupling Navier-Stokes equations and structural modal equations for predicating 3D transonic wing flutter. A dual-time step implicit unfactored Gauss-Seidel iteration with Roe scheme are employed for the flow solver. A modal approach is used for the structural response. The flow and structural solvers are fully coupled vis successive iterations within each physical time step. The accuracy of the modal approach structure solver is validated with finite element solver ANSYS. The results indicate that the first five modes are sufficient to accurately model the wing structure response for present study. The computed flutter boundary of AGARD wing 445.6 for free stream Mach numbers ranging from 0.499 to 1.141 agrees well with the experiment.

UR - http://www.scopus.com/inward/record.url?scp=34250790335&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34250790335&partnerID=8YFLogxK

M3 - Conference contribution

SN - 1563478072

SN - 9781563478079

VL - 11

SP - 8340

EP - 8356

BT - Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting

ER -