The reservoir pressure of a supersonic wind tunnel is \(5 \mathrm{~atm}\). A static pressure probe is moved along the centerline of the nozzle, taking measurements at various stations. For these probe measurements, calculate the local Mach number and area ratio:

a. \(4.00 \mathrm{~atm}\)

b. \( 2.64 \mathrm{~atm}\)

c. \(0.50 \mathrm{~atm}\)