Consider a wing of an airplane is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of 18.0 m and a chord (the length parallel to the flow direction) of 3 m. The airplane is flying at 36,400 m, where the temperature is 250.24K, and the density is 6.7149 X 10- kg/m, with velocity of 220 m/s. Find the viscosity of the air at this altitude (use the graph) Consider the flow is completely laminar, Calculate: 1. the boundary layer thickness at 1/3 of the chord measured from the leading edge. 2. The skin friction coefficient at that point 3. the boundary layer thickness at the trailing edge 4. the total skin friction drag. Consider the flow is completely Turbulent, Calculate: 5. the boundary layer thickness at the trailing edge 6. the total skin friction drag. 7. If the critical Reynolds number for transition is 1.2 X 106, calculate the skin friction drag for the wing.