Question: 3 . ) A rocket motor has a combustion chamber with temperature 3 5 0 0 K and pressure 2 2 atm . The throat

3.) A rocket motor has a combustion chamber with temperature 3500 K and pressure 22
atm . The throat area is 0.1m2. The exit pressure is equal to the atmospheric pressure at
altitude of 20km.=1.23 and Cp=2520JkgK. Calculate:
a. Exit velocity
b. Mass flow rate
c. Thrust force
d. Isp
e. Thrust co-efficient CF
f. Characteristic velocity C**
3 . ) A rocket motor has a combustion chamber

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