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

This paper is devoted to aerodynamic heating calculation of the axisymmetricbodies with discontinuities in the surjace slope. the combined inviscid-boundarulayer method is used to calculate laminar and turbulent aerodynamic heating ofperfect gas and equilibrium air in hypersonic flow. in the existing approximateaeroheating codes, flow properties on the boundary layer edge are calculated[rom an approximate inviscid solution: this approach limits the applicationof such methods to simple bum: cones at low angle of attacks. in thispaper, properties of boundary layer edge are calculated from 1m euler solution:due to a more accurate inviscid flow calculation; this method can be appliedto a broader range of geometries, e.g. multi-cone configurations. resultedaeroheating data from the present approach are compared with experimentaldata 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.