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Implicit solutions of three-dimensional viscous hypersonic flows. (English) Zbl 0748.76080

Summary: An upwind relaxation method to solve the three-dimensional Navier-Stokes equations for hypersonic flows is presented. In the steady-state operator the flux-vector splitting concept is used for the Euler terms. The implicit solution matrix is based on a linearization which reduces the work to compute the elements of the Jacobians and provides a more robust scheme. Additionally, it contains simplified Jacobians of the split inviscid fluxes. A “subgrid” procedure for the viscous layer adjacent to body surfaces is introduced to save computer time. Results are presented for some larminar and turbulent viscous hypersonic flows.

MSC:

76M20 Finite difference methods applied to problems in fluid mechanics
76K05 Hypersonic flows
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