Laminar and Turbulent Aeroheating Predictions around Multi-Cone Configurations in Hypersonic Equilibrium-Air Flow

This paper is devoted to aerodynamic heating calculation of the axisymmetric bodies with discontinuities in the surjace slope. The combined inviscid-boundaru layer method is used to calculate laminar and turbulent aerodynamic heating of perfect gas and equilibrium air in hypersonic flow. In the existing approximate aeroheating codes, flow properties on the boundary layer edge are calculated [rom an approximate inviscid solution: This approach limits the application of such methods to simple bum: cones at low angle of attacks. In this paper, properties of boundary layer edge are calculated from 1m Euler solution: Due to a more accurate inviscid flow calculation; this method can be applied to a broader range of geometries, e.g. multi-cone configurations. Resulted aeroheating data from the present approach are compared with experimental data and found to be in good agreement under laminar and turbulent conditions. These include accurate predictions of aero heating over the multi-cone bodies, which prove high capability of the method for this type of configurations.