The phenomenon of aerodynamic heating is created as a consequence of body-flow interaction. It is originated from viscous flow characteristics inside the boundary layer in the vicinity of body. The adjacent flow temperature increases, leading to an increase in body wall temperature depending on flow regime, surrounding air density, body velocity, wall material, flight time, etc.. The present work provides an illustrative calculation procedure based on closed-form relations. A computer program was implemented to be used as a quick, easy, and accurate calculation tool for the expected wall temperature distribution and its variation with flight time for a conical fore-body during a complete flight at zero incidence. The code was applied on a number of real cases with a variety of flight conditions. Results were compared with
published and previous work and showed very good agreement.