Abstract
A computational method has been developed to predict three-dimensional hypersonic laminar or turbulent shock-layer flows for perfect gas or equilibrium air. A two-layer eddy-viscosity model is used for the turbulent regime. The thermodynamic and transport properties for air are obtained by interpolation within a twodimensional table or from curve-fit data. Comparisons are made for air in chemical equilibrium and perfect gas for laminar and turbulent flow over a 7-deg half-angle spherically blunted cone at various flight altitudes with a cold, moderately cool, and an adiabatic wall for angles of attack up to 20 deg. Surface pressure and wall heattransfer distributions, force and moment coefficients, and execution times are compared for some sample cases. This method can be used to predict viscous flowfields in chemical equilibrium over axisymmetric re-entry vehicles at angles of attack up to 25 deg.
Published Version
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