A rocket motor is operating steadily, as shown in Fig. P3.34. The products of combustion flowing out the exhaust nozzle approximate a perfect gas with a molecular weight of 28. Liquid oxygen enters at 0.5 slug/s and liquid fuel at 0.1 slug/s. Combustion conditions: 4000° R, 400 lbf/in2. Exit conditions: 15 lbf/in2, 1100° F, D2=5.5 in. For the given conditions calculate V2 in ft/s.