Heat and Mass Transfer on the Side Surfaces of Blunt Nose Parts of Hypersonic Aircraft

Based on generally accepted assumptions, an approximate analytical solution of the problem of the flow and heat and mass transfer in a chemically reacting gasdynamic boundary layer on the side surfaces of a streamlined nose at hypersonic velocities of the oncoming flow is obtained. Using the obtained solutions, the convective and diffusive heat fluxes to the surface of a streamlined cone are calculated, and the thermal state and temperature of the surface of the streamlined cone are determined based on the balance of radiant and conductive fluxes supplied to and removed from it into the body. The results of a numerical solution for surface temperatures in the range of Mach numbers 5 <= Mu <= 25 and flight altitudes 20 <= H <= 80 km are obtained and analyzed.