An airfoil section is placed in a large wind tunnel that produces air speeds of 300 mi/h at free-stream conditions of 290 K and 1 atm pressure. The airfoil is heated to a uniform temperature of 310 K. Estimate the heat lost from both the top and bottom of the airfoil using charts in this chapter. Assume that the airfoil section may be approximated as a flat plate having a length equal to the peripheral distance from the front stagnation point to the rear edge and that this peripheral dimension is measured as 5 m.