Simulation of Heat and Mass Transfer on Blunt Bodies under Aerodynamic Heating of High-Speed Aircraft

The heat and mass transfer between the dissociating boundary layer and the surface of blunt nose cones of high-speed aircraft in a wide range of Mach numbers is considered. Using Dorodnitsyn–Liz variables, the system of boundary layer equations is reduced to a system of nonlinear ordinary differential equations. Using reasonable assumptions, approximate analytical solutions were obtained for dynamic, thermal, and diffusion boundary layers, which made it possible to determine thermal and diffusion heat fluxes, which at the gas–solid boundary are coupled with the equation of heat conduction in the body with the coupling parameter being the temperature of the gas–solid boundary. From the found heat fluxes, the temperature fields in the body were determined in a wide range of free-stream Mach numbers and the catalytic recombination coefficient. The resulting heat fluxes on the frontal part of the nose cone exactly coincide with the experimental data.