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A flapping NACA0012 wing with spanwise rigid and flexible configurations is simulated using the Delaunay graph mapping based mesh deformation technique. This mesh deformation scheme is quite efficient and gives a good alternate to the spring analogy due to its non-iterative nature and simple implementation. It is also well suited for the parallel implementation due to its preservation of the original mesh topology. The preliminary simulated case is spanwise rigid at Garrick frequency of 1.82 and Reynolds number 30,000, corresponding to the experimental data by Heathcote et. al [AIAA- 2006-2870]. The results obtained for this case are in a good agreement with the experimental data for the instantaneous thrust. The simulation also predicts the lag in flapping motion cycle and generated thrust due to the dynamic effects of the flapping cycle and a corresponding phase lag is depicted in the thrust during the flapping cycle. The detailed paper will also include the implementation and results of the spanwise flexible flapping NACA0012 wing.

50th aiaa aerospace sciences meeting including the new horizons forum and aerospace exposition

Delaunay Graph Mapping-Based Mesh Deformation for Simulation of a Spanwise Rigid and flexible Flapping NACA0012 Wing Using DES with Parallel Implementation