Partitioned procedures for the transient solution of coupled aeroelastic problems. II: Energy transfer analysis and three-dimensional applications.

*(English)*Zbl 1015.74009[For part I see the authors and B. Larrouturou, ibid. 124, No. 1-2, 79-112 (1995; Zbl 1067.74521).]

Summary: We consider the solution of large-scale nonlinear dynamic aeroelasticity problems in time-domain using a fluid-structure partitioned procedure. We present a mathematical framework for assessing some important numerical properties of the chosen partitioned procedure and examine its performance in realistic applications. Our analysis framework is based on the estimation of the energy that is artificially introduced at fluid-structure interface by the staggering process that is inherent to most partitioned solution methods. This framework also suggests alternative approaches for time-discretizing the transfer of aerodynamic data from fluid subsystem to structure subsystem, that improves the accuracy and stability properties of the method. We apply this framework to the analysis of several partitioned procedures that have been previously proposed for the solution of nonlinear transient aeroelastic problems. Using two- and three-dimensional, transonic and supersonic wing and panel aeroelastic applications, we validate this framework and highlight its impact on the design and selection of staggering algorithm for the solution of coupled fluid-structure equations.

Summary: We consider the solution of large-scale nonlinear dynamic aeroelasticity problems in time-domain using a fluid-structure partitioned procedure. We present a mathematical framework for assessing some important numerical properties of the chosen partitioned procedure and examine its performance in realistic applications. Our analysis framework is based on the estimation of the energy that is artificially introduced at fluid-structure interface by the staggering process that is inherent to most partitioned solution methods. This framework also suggests alternative approaches for time-discretizing the transfer of aerodynamic data from fluid subsystem to structure subsystem, that improves the accuracy and stability properties of the method. We apply this framework to the analysis of several partitioned procedures that have been previously proposed for the solution of nonlinear transient aeroelastic problems. Using two- and three-dimensional, transonic and supersonic wing and panel aeroelastic applications, we validate this framework and highlight its impact on the design and selection of staggering algorithm for the solution of coupled fluid-structure equations.

##### MSC:

74F10 | Fluid-solid interactions (including aero- and hydro-elasticity, porosity, etc.) |

76G25 | General aerodynamics and subsonic flows |

74S05 | Finite element methods applied to problems in solid mechanics |

74S20 | Finite difference methods applied to problems in solid mechanics |

##### Keywords:

three-dimensional transonic wing problem; panel flutter; three-dimensional supersonic wing problem; energy estimate; large-scale nonlinear dynamic aeroelasticity; time-domain; fluid-structure partitioned procedure; fluid subsystem; structure subsystem; staggering algorithm
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\textit{S. Piperno} and \textit{C. Farhat}, Comput. Methods Appl. Mech. Eng. 190, No. 24--25, 3147--3170 (2001; Zbl 1015.74009)

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##### References:

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