The unsteady, three-dimensional full Navier-Stokes equations are solved using a Beam-Warming implicit algorithm in this paper. Computations of the flow over a 76 deg sweep delta wing at the angle of 20 deg and 36.5 deg are presented. The structures of leading-edge and tip vortices of both these two angles are identified and compared by tracing particles in three-dimensional space. Computed oil flow paterns of flow fields are investigated. Reverse flow (or a bubble) and a three-dimensional stagnation point at the head of the breakdown region are observed for the 36.5 deg angle of attack.
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