Computation of Flows over a 3D Wing with a Vortex Generator
Flow fields over a 3D delta wing having a vortex fence at the apex region are investigated numerically by solving the unsteady compressible Navier-Stokes equations. A second order explicit finite volume scheme is used to simulate the temporal evolution of the flow field. The computational efficiency and the spatial resolution are improved by adopting various multi-zone techniques. Simulations are conducted to show the typical features of the flow field in the subsonic range. Detailed flow pictures near the vortex fence and the successive interaction of the shed vortex with the leading edge vortex of the delta wing are presented.
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