Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow

In this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. in this method, a maslen’s second-order pressure expression is used instead of the normal momentum equation. the combination of maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently compute hypersonic flow fields of perfect gas around blunt-body configurations. the results show that, this combination leads to more accurate solutions and less extensive computer run times in the preliminary design environment. furthermore, the utility of cebeci-smith turbulence model is adequate for application to long slender bodies. the results of these computations are found to be in good agreement with available numerical and experimental data.