Prediction of SBLI Induced Flexible Panel Motion using Wall-Modeled LES Coupled to an Aeroelastic Solver
Wall-modeled large eddy simulation (WMLES) and a theoretical-computational aeroelastic solver are used to predict the motion of a thin flexible panel under an impinging shock wave. Panel displacements imposed by the resulting shock-wave/boundary-layer interactions are compared to measured displacements from an experiment at matching conditions. The maximum static deformation predicted by the WMLES is found to be about 10% off of the experiment, showing better agreement than a previously developed model. The panel displacement is used to deform the computational domain, and an additional WMLES is conducted and compared to the original. Both simulated flowfields show strong similarities to each other and modest discrepancies with the experiment in static wall pressure and wall pressure fluctuations.
