The following table gives the values of the drag coefficient of a thin aerofoil at different free-stream Mach numbers. Calculate the drag of the aerofoil at sea level condition with these Mach numbers. The area of the aerofoil is \(40 \mathrm{~m}^{2}\). Plot a graph of drag \(D\) and drag coefficient \(C_{D}\) vs. Mach number \(M_{f s}\).

(The values in the table are modified from the example in Kermode (2012)

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1.05 1.1 1.2 0.8 0.85 0.9 0.95 1.0 1.3 1.4 0.011 0.011 0.016 0.026 0.05 0.068 0.063 0.055 0.046 0.04 0.034 0.03 0.028 My 0.6 0.7 0.75 Drag