Consider the arrangement shown in Fig. 4.34. A \(15^{\circ}\) half-angle diamond wedge airfoil is in a supersonic flow at zero angle of attack. A Pitot tube is inserted into the flow at the location shown in Fig. 4.34. The pressure measured by the Pitot tube is \(2.596 \mathrm{~atm}\). At point \(a\) on the backface, the pressure is \(0.1 \mathrm{~atm}\). Calculate the free-stream Mach number \(M_{1}\).

Figure 4.34:

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Pito: lube