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 \[C_{p}=1-\left ( \frac{130}{98.8} \right )^{2}
\\=-0.73\]
