Implicit Large Eddy Simulation of Transitional Flow over a SD7003 Wing Using High-order Spectral Difference Method

The transitional flow with a laminar separation bubble over a SD7003 wing at a low Reynolds number = × and angle of attack = . is numerically computed using implicit large eddy simulation with a spectral difference method on unstructured hexahedral meshes. The averaged and statistical results are compared with previously published results. A laminar separation bubble forms after the flow detaches from the suction side of the wing. After the vortex breakdown, the separated flow transitions to turbulent flow and reattaches to the wall. The origin and growth of the initial disturbances are investigated. The vortex breakdown process and the transition mechanism are described and discussed.

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