(Solved): Consider a drone which is propelled by a solid fuel burning rocket motor. See figure below for a sch ...

Consider a drone which is propelled by a solid fuel burning rocket motor. See figure below for a schematic of a solid fuel burning rocket motor. The air exhausting the combustion area of the motor (before the nozzle where the grain is) has a stagnation pressure of 600 kPa and stagnation temperature of 600 K . For all gases in this problem you can assume

and

a. (20 pts) If the motor is coupled to a nozzle which only contains a converging section with an exit area of

calculate the mass flow through the nozzle at an altitude of 2000 m where the atmospheric is 80 kPa b. ( 10 pts ) For the same configuration as part a. what would the mass flow rate be if the drone climbed to an altitude of 8000 m where the atmospheric pressure is 35 kPa c. (10 pts) If the converging nozzle was replaced with converging-diverging nozzle that was designed to operate on design at an altitude 8000 m what would the exit area have to be if the throat area is

? d. ( 25 pts ) Derive an expression and use it to determine the thrust generated by the configuration of part c .