A simultanbeously coupled viscous-inviscid (IVI) procedure-for computing the unsteady flow associated with the onset of stall flutter in turbomachinery cascades is presented. Using this method, the flow is divided into two parts: a viscous flow near the airfoil and in the wake, and an inviscid flow in the rest of the flow field. The viscous flow is modeled using a finite difference discretization of the boundary layer equations. The inviscid flow is modeled using a variational finite element discretization of the full potential equation. The viscous and inviscid flow regions are then simultaneously coupled using a transpiration type boundary condition along the airfoil and wake.
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