Find the thrust produced by a rocket engine at an altitude of 55\, km, if the exit area of the rocket engine is 2.5\,m^2. Mass flow of the propellants is 30\,kg/s and has a exit velocity of 4500\,m/s and a exit pressure of 2.2 \times {10^4}\,N/m^2.
Find the thrust produced by a rocket engine at an altitude of 55\, km, if the exit area of the rocket engine is 2.5\,m^2. Mass flow of the propellants is 30\,kg/s and has a exit velocity of 4500\,m/s and a exit pressure of 2.2 \times {10^4}\,N/m^2.
At an altitude of 55 km, ambient pressure, {p_\infty } = 48.4\,N/{m^2}
Thrust produced by a rocket engine is given by
T = \dot m{V_e} + \left( {{p_e} – {p_\infty }} \right){A_e}
\Rightarrow T = \left( {30 \times 4500} \right) + \left( {2.2 \times {{10}^4} – 48.4} \right)2.5 = 189879\,N
