Heating and Aerothermodynamic Analysis of Aerospace Vehicles Using an Engineering Method

In this paper, a very fast engineering method is introduced to estimate convection heat flux on axisymmetric and hypersonic projectiles. For calculation of properties flow at the edge of boundary layer (pressure, temperature and velocity), the results of in viscid flow analysis reported in tables (from a Russian reference) was used and for viscous region, Zoby’s convectionheat transfer equations was implemented. Moreover, real gas assumption was used for thermo physical properties of the fluid, The main goal of this research is to develop avery fast computer code for aero thermodynamic calculations of hypersonic cvehicles that may be used as a tool forde signing of heat shields. The results of the present method were compared with those of the other researchers and there is good agreement between them.