Question

Given an optimally-expanded rocket motor, calculate the mass flow rate of the propellat, the nozzle expansions ratio, and the exit veloctiy of the propellant gas.

Given: A(throat) = 0.442 in^2 gamma=1.2 Po = 750 psia P1 = 10.2 psia To = 3500 degrees F

gamma is the heat capacity ratio

Answer 1

Answer:-

Given Data:- A(throat) = 0.442 in^2

=1.2

Po = 750 psia

P1 = 10.2 psia

To = 3500 degrees F

m= A *Pt / Tt [ /R ] ( +1/2) ^{(-+1/ 2(-1))}

m = 0.442* 760.2 / 3500 [ 1.2 / 8.314](1.2+0.5) ^{(-1.2+1 / 2(1.2-1)}

m = 0.113 .

Hence mass flow rate is 0.113