Heat Fluxes and Surface Temperatures at Components of High-Speed Aircraft in a Dissociating Air Flow

An approximate analytical solution is obtained for the system of equations describing the high-temperature dissociating boundary layer at the lateral surfaces of blunt nose cones in high-speed aircraft, so as to determine the heat fluxes and surface temperatures in aerodynamic heating. Significant use is made of the Reynolds analogy regarding the velocity, temperature, and concentration profiles of the atomic component in a binary gas. To determine the surface temperature of a high-speed aircraft, radiant and conductive heat transfer within the structure is taken into account.