In contrast to the liquid rocket in Fig. P3.34, the solid-propellant rocket in Fig. P3.35 is self-contained and has no entrance ducts. Using a control volume analysis for the conditions shown in Fig. P3.35 (combustion at 1500 K, 950 kPa; exit section De=18 cm, pe=90 kPa, Ve=1150 m/s, Te=750 K), compute the rate of mass loss of the propellant, assuming that the exit gas has a molecular weight of 28.