Consider a rocket engine with the following parameters -1500 kN of thrust -It uses fuel with density 672 kg/m3 and an ox

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Consider a rocket engine with the following
parameters
-1500 kN of thrust
-It uses fuel with density 672 kg/m3 and an oxidizer with
density 1400 kg/m3.
-The operating combustion chamber pressure is 145 atm and the
oxidizer-to-fuel ratio is 2.66, which gives a combustion chamber
stagnation temperature of 3400 ◦K.
Assuming the combustion products to have γ = 1.16 and a
molecular weight of 24 kg/kmol. and using ideal
conditions.
(a) Determine the sea level equivalent velocity ueq if the
sea level thrust coefficient is 1.65.
(b) What is the mass flow rates of the fuel and the oxidizer to
achieve the design thrust?