Consider a solid propellant rocket engine with an end-burning configuration as shown in Fig. 9.30a. The solid propellant is ammonium nitrate. The burning characteristics of this propellant when the initial grain temperature is 60°F are given by the following measured data: linear burning rate is 0.04 in/s at a combustion pressure of 500 lb/in2, and 0.058 in/s at a combustion pressure of 1000 lb/in2. The rocket engine is operating at a combustion pressure of 1500 lb/in2. Calculate the distance the burning surface will recede in 5 seconds.
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