In Prob. 3.34 we knew nothing about compressible flow at the time so merely assumed exit conditions p2 and T2 and computed V2 as an application of the continuity equation. Suppose that the throat diameter is 3 in. For the given stagnation conditions in the rocket chamber in Fig P3.34 and assuming k = 1.4 and a molecular weight of 26, compute the actual exit velocity, pressure, and temperature according to one-dimensional theory. If pa = 14.7 lbf/in2 absolute, compute the thrust from the analysis of Prob. 3.68. This thrust is entirely independent of the stagnation temperature (check this by changing to 2000°R if you like). Why?

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Liquid oxygen: 0.5 slug/s 4000° R 400 lbf/in D2 5.5 in (3Liquid fuel: 0.1 slug/s