Using a propellant of molecular weight 15 and flame temperature 3300 K, determine the rocket throat and exhaust areas required for a thrust of 500 kN and an ideal specific impulse of 300 sec. The ambient pressure is 0.1 MPa, and the specific-heat ratio of the propellant is 1.4. How much thrust would this rocket
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Using a propellant of molecular weight 15 and flame temperature 3300 K, determine the rocket throat...
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