“…Before studying the aerodynamic forces and flow field of the wing model, CFD code [14], mesh density, the first mesh spacing, computation time step, and computational domain size used in this study have been validated, as shown in Figure 4, here, the time t is non-dimensionalized by the period of spinning around wing span axis. As a result, a numerical solution independent of mesh and time steps can be achieved when the mesh dimension is 70 × 75 × 152 (in the normal, chordwise, and spanwise directions, respectively), the domain size is 30c, the first mesh spacing at the wall is 0.001c, and 400 time steps are used in one spinning cycle.…”