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2005•Journal of Air Force Engineering UniversityRequires access

An Analysis of Structure Response for Transonic Static Aeroelasticity

Zhi‐Min Chen

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Abstract

A dynamic meshes and CVT interpolated technology are developed to generate interface mapping for CFD/CSD coupling procedure. Computational structural dynamics (CSD) are modeled using finite element equations. Solving aerodynamic force employs Navier-Stokes discretized based cell-centered finite volume framework with dual-time technology. An aeroelastic coupling procedure will perform with loosing coupling CFD/CSD at the same physics time step. Finally, the CFD / CSD coupling computational convergence solution is obtained for a swept wing at M_∞=0.8395,α=5.06°, using the developed nonlinear aeroelastic methodology.History of response of the structure and aerodynamic characteristic with time is analyzed. The study shows the developed CFD / CSD coupling procedure is able to compute nonlinear aeroelastic analysis.

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What this paper is about

A dynamic meshes and CVT interpolated technology are developed to generate interface mapping for CFD/CSD coupling procedure. Computational structural dynamics (CSD) are modeled using finite element equations. Solving aerodynamic force employs Navier-Stokes discretized based cell-centered finite volume framework with dual-time technology. An aeroelastic coupling procedure will perform with loosing coupling CFD/CSD at the same physics time step. Finally, the CFD / CSD coupling computational convergence solution is obtained for a swept wing at M_∞=0.8395,α=5.06°, using the developed nonlinear aeroelastic methodology.History of response of the structure and aerodynamic characteristic with time is analyzed. The study shows the developed CFD / CSD coupling procedure is able to compute nonlinear aeroelastic analysis.

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Available abstract

A dynamic meshes and CVT interpolated technology are developed to generate interface mapping for CFD/CSD coupling procedure. Computational structural dynamics (CSD) are modeled using finite element equations. Solving aerodynamic force employs Navier-Stokes discretized based cell-centered finite volume framework with dual-time technology. An aeroelastic coupling procedure will perform with loosing coupling CFD/CSD at the same physics time step. Finally, the CFD / CSD coupling computational convergence solution is obtained for a swept wing at M_∞=0.8395,α=5.06°, using the developed nonlinear aeroelastic methodology.History of response of the structure and aerodynamic characteristic with time is analyzed. The study shows the developed CFD / CSD coupling procedure is able to compute nonlinear aeroelastic analysis.

Key concepts: Aeroelasticity, Transonic, Computational fluid dynamics, Aerodynamics, Finite element method, Nonlinear system, Coupling (piping), Discretization

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