Wing flutter prediction using a reduced dynamic mesh method

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Journal of Vibration and Shock ›› 2017, Vol. 36 ›› Issue (4) : 185-191.

ZHONG Jize,XU Zili

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Abstract

In this paper,a reduced method for flow mesh deformation around a wing was developed based on the elastic solid method. The flow mesh domain was assumed to be a pseudo elastic solid. The total vibration equation for the wing with the pseudo elastic solid together was derived using the static equilibrium equation of the pseudo elastic solid and the vibration equation of the wing. The nodal displacements for the wing and flow mesh were computed through modal superposition and the deformed flow mesh was obtained. Considering that wing flutter often appeared as the 1st bending and torsion flutter,the nodal displacements for the flow mesh could be calculated by modal superposition of the 1st bending and torsion mode. To ensure the computational accuracy,the 2nd bending and torsion mode were also considered. The flutter boundary of the AGARD Wing 445.6 was predicted using the present dynamic mesh method coupled with the RANS equations and the Spalart-Allamras turbulent model. The relative error of the calculated results to the experimental data was less than 2%. The computing time was reduced by 54.8% compared with the pre-existing elastic solid method.

Key words

wing flutter / fluid structure interaction / dynamic mesh / pseudo elastic solid / modal superposition

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ZHONG Jize,XU Zili. Wing flutter prediction using a reduced dynamic mesh method[J]. Journal of Vibration and Shock, 2017, 36(4): 185-191

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