Experimental measurements of the temperature distribution in flow of atmospheric pressure air over the wing of an airplane indicate that the temperature distribution near the surface can be approximated by a linear equation(T ?? Ts) = α y (T?? ?? Ts)Where α = α constant = 2 m??1Ts = surface temperature, KT?? = free stream temperature, Ky = perpendicular distance from surface (mm)(a) Estimate the convective heat transfer coefficient ifTs = 50?C and T?? = ?? 50?C.(b) Calculate the heat flux in W/m2GIVENAir flow over an airplane wingTemperature distribution is given by the expression aboveSurface temperature (Ts) = 50?CAmbient temperature (T??) = ?? 50?CASSUMPTIONSSteady state conditionsUniform surfacetemperature

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Alr T.-- 50°C T= 50° C Wing Surface