A N-S solution of a 3D wing with flap deflection is presented. The complex flow around this kind of configuration is effectively solved by using a combination of patched grid and domain decomposition techniques. An internal coupling condition satisfying the conservation of flux is used in the domain decomposition method. The spatial flux terms are discretized by using central difference scheme and the time integration is performed by using explicit scheme in the flow solver, Based on this N-S solution the separated now field is analyzed. The main flap flow features, such as the side-edge region flow pattern and 3D-leading edge separated flow pattern, are shown and discussed in detail. [References: 9]
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