A solid propellant rocket engine gases at 3000 K stagnation temperature and 6000 kPa stagnation pressure...

A solid propellant rocket engine gases at 3000 K stagnation temperature and 6000 kPa stagnation pressure It manufactures. The exit and throat areas of the nozzle are 0,01 m2 respectively. and 0.005 m2 Adiabatic base of the produced gases 1,4 and the gas constant is 320 J / kg.K. Find the thrust produced by the rocket at a height of 25 000 m (kN).

Expert Solution

Answer :

Thrust produced by the rocket = 27 kN

Explanation :

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samet mamat answered 2 months ago

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