A finite-volume unstructured-grid FEM scheme with multistage Runge-Kutta time stepping is applied to the three-dimensional time-dependent Euler equations for inviscid flows on complex aircraft configurations undergoing structural deformation. The derivation of the model, the solution procedure, and the computer implementation are described, and results are presented graphically for a NASA Langley supersonic fighter aircraft model in steady and unsteady (harmonic oscillation in complete-vehicle bending mode) flow regimes. Good agreement between FEM predictions and experimental data is demonstrated.


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    Title :

    Unsteady Euler algorithm with unstructured dynamic mesh for complex-aircraft aeroelastic analysis


    Contributors:

    Conference:

    AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference ; 1989 ; Mobile, AL, United States


    Publication date :

    1989-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English