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Computational Aeroelasticity Using a Pressure-based Solver

Ramji Kamakoti1, Yongsheng Lian1, Sean Regisford1, Andrew Kurdila1, Wei Shyy1
Dept. of Mechanical and Aerospace Engineering
University of Florida
Gainsville, FL, USA

Computer Modeling in Engineering & Sciences 2002, 3(6), 773-790. https://doi.org/10.3970/cmes.2002.003.773

Abstract

The non-linear fluid-structure interaction problem is studied for two different wing configurations based on moving grid techniques. These configurations demonstrate the interaction between a rigid structure and fluid, as well as the interaction between a flexible structure and fluid. A closely-coupled approach is used to perform the combined fluid and structure interaction computations. The flow solver is an unsteady, implicit, three-dimensional, multi-block, pressure-based Navier-Stokes solver. The structure solver for the AGARD wing model is based on a linear, time-invariant model derived via classical structural finite elements whereas the flexible structural solver is based on a non-linear dynamic membrane model with the material obeying the hyperelastic Mooney's model. Suitable interfacing techniques are incorporated to couple and synchronize the flow and structure solvers. We present unsteady computations performed on both rigid and membrane wings to highlight the computational characteristics.

Cite This Article

Kamakoti, R., Lian, Y., Regisford, S., Kurdila, A., Shyy, W. (2002). Computational Aeroelasticity Using a Pressure-based Solver. CMES-Computer Modeling in Engineering & Sciences, 3(6), 773–790.



This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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