A computational study of non-classical aileron buzz is presented, which focuses on computational grid details for accurate simulations of this type of nonlinear transonic phenomenon. The analysis points out that mesh refinement is crucial to obtain reliable results and that the choice between a smoothed and non-smoothed geometry has an influence on the system response, both quantitatively and qualitatively. As a matter of fact, grid details affect the simulation of shock dynamics, which is the driving mechanism for non-classical aileron buzz.
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