A rocket has a first-stage engine sea-level exhaust velocity of 2.3 km/s, with a first-stage burn time of 120 s. The rocket diameter is 3.3 m, and the drag coefficient is 0.6 (taken as a constant regardless of Mach number). The gross mass is 500 metric tonnes. The first stage propellant mass is 360 metric tonnes. Calculate the Mach number of the rocket when it passes through max q. The rocket exit area is 6 m2, and the nozzle exit pressure is 25 kPa.nd final answer must be within +/- 2% of the correct answer.