ESDU Aero W.S.00.03.18 provides a graph of the stagnation temperature in air taking into account the variation of the specific heat capacity at constant pressure of the air with temperature. Away from the stagnation point the local temperature on the surface of a body is obtained by the technique of applying a recovery factor to the difference between the stagnation temperature and the local static temperature just outside the boundary layer. Two further graphs plot the surface temperature in fully-attached flow as a function of the stagnation temperature and of the local static temperature and Mach number just outside the boundary layer. One graph is for laminar boundary layers assuming the recovery factor is 0.85 and one is for turbulent boundary layers assuming the recovery factor is 0.9.