عنوان مقاله [English]
In this study, the numerical simulations of hypersonic axisymmetric viscous flows over blunt noses, including equilibrium gas effects,
are performed by using shock fitting and shock capturing schemes to examine the effects of shock boundary treatment on the accuracy of computations. The numerical solution of the thin-layer Navier-Stokes (TLNS) equations in the nose region is obtained by using the implicit non-iterative finite-difference algorithm of Beam and Warming and an appropriate formulation of the shock boundary condition for the shock fitting procedure, with considering real gas effects, is implemented. The thermodynamic and transport properties of air are calculated by using the simplified curve fits developed by Srinivasan et. al.. The numerical solutions
of hypersonic equilibrium flow over a sphere at Mach number of 16.89 are performed and the calculations for the flowfield and the shock shape are compared with available numerical results. The computations are presented for both equilibrium and perfect gas
models and the results of flowfield and shock shape for the shock fitting and shock capturing procedures are compared with each
other. In addition, the role of numerical dissipation and the effects of grid size on the accuracy of the results are investigated.