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| Numerical simulation of transonic flutter based on agglomeration multigrid method |
| Revised:March 31, 2003 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7511/jslx20051020 |
| KeyWord:flutter,transonic,unstructured grid,CFD,CSD,agglomeration multigrid |
| XIA Jian~{*1} LIU Feng~2 |
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| Abstract: |
| An efficient fluid-structure interaction solver based on agglomeration multigrid is developed in this paper. The unsteady Euler equations are fully coupled with the modal dynamic equations of a typical Isogai wing section and integrated forward in time. CFD solver is based on an unstructured finite volume algorithm and the Roe's upwind scheme is used for fluxes computation. The whole mesh moves rigidly with the airfoil without any deformation, which simplifies the procedure to compute the grid speed on control volume boundary. Aeroelastic system is decomposed for the two degree of freedom and integrated using a direct procedure. The whole system (fluid equations and structural modal equations) is marched implicitly in time using a dual time stepping method: at every real time step, a fully converged CFD-CSD solution is achieved by pseudo time marching which is accelerated by the agglomeration multigrid method. A steady transonic case of NACA0012 is first given to verify the efficiency of the agglomeration multigrid. Five level grids are used and the convergent rate is increased at least one order without losing any accuracy. Finally the Isogai test case which has been widely numerically investigated is studied. Flutter boundary prediction for a typical wing section NACA 64A010 is present and compared well with correlational references. |
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