The flow and heat transfer characteristics of high-speed air over an airfoil initially at temperatures of 200 K and 300 K, respectively, are investigated. Two types of airfoil are considered, the NACA0012 and the symmetrical double wedge airfoil. The free-stream air flow velocity is set at various Mach number regimes (transonic and hypersonic). The LSTC propriety transient solver LS-DYNA is used to generate different resulting shock wave formation using the CESE (conservation-element solution-element) method. It was found that for subsonic flows, increasing the Mach number towards the transonic flow would decrease the heat flux from the airfoil to the air flow; and for hypersonic flows, increasing the Mach numbers would increase heat flux going into the airfoil. This indicates that frictional heating exists for objects subjected under subsonic to transonic and transonic to hypersonic air flows.