$($a$)$ rocket motor has the specifications given in Table $1$ below. Assuming optimum

expansion calculate:

i$.$ The velocity of gas at the throat $(\frac{m}{s})$

ii$.$ The mass flow rate $(k\frac{g}{s})$

iii. The specific impulse $I_{sp}$

iv$.$ The thrust.

v$.$ The gas temperature at the throat.

vi$.$ The area of the norzle exit.

vii. The mach number at the exit of the nowzle

$($b$)$ Evaluate the thrust coeflicient $C_F$ of this system using two different methods. Why,

in general, might these methods provide different results when applied to a real motor

system?

$($c$)$ What is the change in enthalpy between the gas at the throat and at the exit of the

nozzle?