In this study, the hypersonic ionized non-equilibrium flows over rounded nose geometries are numerically investigated by a robust conservation element and solution element (CE/SE) code, which is based on hybrid meshes consisting of triangular and quadrilateral elements. The dissociating and ionization chemical reactions as well as the vibrational energy relaxation are taken into account. The stiff source terms are solved by an implicit trapezoidal method of integration. Comparison with laboratory and flight tests are provided to demonstrate the accuracy and reliability of the present CE/SE code in simulating ionized hypersonic non-equilibrium flows.
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