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
\[T = \dot m{V_e} + \left( {{p_e} – {p_\infty }} \right){A_e}\]
\[ \Rightarrow T = \left( {30 \times 4500} \right) + \left( {2.2 \times {{10}^4} – 48.4} \right)2.5 = 189879\,N\]
