An airplane flying at standard sea level has a velocity of 98.8 \;m/s. At a given point on the surface of the wing of the airplane the flow velocity is 130 \;m/s. Calculate the pressure coefficient at this point.
We need to calculate here the pressure coefficient at a point on the surface of the wing of the airplane. Pressure coefficient is given as C_{p}=1-\left ( \frac{V}{V_{\infty}} \right )^{2}
Therefore C_{p}=1-\left ( \frac{130}{98.8} \right )^{2} \\=-0.73
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