Finite-difference procedures are used to solve the Eulerian gasdynamic equations whose flux vectors are homegenease function (of degree one) subject to cascades boundary conditions.
The natural coordinate system is used for grid generation, and because an implicit finite-difference algorithm for the flow equations is used, time steps are not severely limited when grid points are finely distributed. The algorithm is second-order time accurate, noniterative, and in a spatially factored form. Second or fourth-order central and secondorder one-sided spatial differencing are accomondated within the solution of a block tridiagonal system.
Because High inlet flow velocity is used for DCA caseade, the flow is transonic which have the shock. The purposes of this research are to study the shock treatment and the behavior of DCA cascade in transonic flow.
