The numerical simulation of inviscid transonic flows by means of a "modified lambda formulation" takes into account the shock transition from supersonic to subsonic flow conditions, thus allowing the coupling of the supersonic region with the shocked subsonic one and, as a consequence, the upstream movement of the shock. The present methodology is applied to one- and two-dimensional transonic flows. Although the two-dimensional flow calculations involve Cartesian coordinates and are limited to the thin-airfoil approximation, the method can be generalized to arbitrary two- and three-dimensional flow cases. In all of the computed cases, the shock is found to have appropriate strength and position for steady flow conditions and to move upstream properly when a change in the downstream pressure warrants it.
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