The aerodynamic heating of airfoils is one of main problems of hypersonic flight vehicles. In this paper, firstly, based on the reference enthalpy method and the empirical formula, the aerodynamic heating flux of hypersonic flight vehicles was studied using the strip theory. Secondly, for both of the boosted period and the cruise period, the temperature distribution was calculated under different angles of the attack and airfoils. Furthermore, based on above steps of solutions, a solution flow chart of the aerodynamic heating of airfoils of hypersonic flight vehicles was given. Considering an example about a biconvex airfoil, its aerodynamic heating was calculated by the method in this paper. The results indicate that the angle of the attack, the sweepback angle of wing leading edge and the relative thickness of the airfoil significantly influence on the temperature distribution of airfoils. This method is helpful for preliminary design of hypersonic flight vehicles.