A certain ideal rocket with a nozzle area ratio of 2.3 and a throat area of 5 in. 2 delivers gases at k = 1.30 and R = 66 ft-lbf/lbm-? R at a chamber pressure of 300 psia and a constant chamber temperature of 5300? R against a back atmospheric pressure of 10 psia. By means of an appropriate valve arrangement, it is possible to throttle the propellant flow to the thrust chamber. Calculate and plot against pressure the following quantities for 300, 200, and 100 psia chamber pressure:

(a) pressure ratio between chamber and atmosphere;

(b) effective exhaust velocity for area ratio involved;

(c) ideal exhaust velocity for optimum and actual area ratio;

(d) propellant flow;

(e) thrust;

(f) specific impulse;

(g) exit pressure;

(h) exit temperature.