Approximate Viscous Shock-Layer Analysis of Axisymmetric bodies in Perfect gas hypersonic

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 is developed to accurately and efficiently compute hypersonic flow fields of perfect gas around blunt-body configurations. This study includes results for 5 to 15 deg half angle bodies with nose radii ranging from 1.1 to 1.5 inch for blunt nosed bodies. The results show that, this combination lead 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.

کلیدواژه ها:

Approximate ، Aerodynamic Heating ، Hypersonic Flow ، perfect gas