Calculate the local skin friction coefficient and shear stress at a point 0.5 m from the leading edge of flat-plate airfoil flying at 60 m/s at a height of 6 km? First, assume that the boundary layer remain laminar. Second, assume that the boundary layer is turbulent. For the air viscosity at that altitude, use the value 1.5949·10-5 kg/(s·m).

answer:

the answer is d

explanation:

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