For a rocket engine, the velocity ratio $r$ is $V_{a} / V_{e},$ where $V_{a}$ is the vehicle velocity and $V_{e}$ is the exit velocity of the exhaust gases. Assume the flow to be optimally expanded through the nozzle. For $\boldsymbol{r}=2$, if $F$ is the thrust produced and $\dot{m}$ is the mass flow rate of exhaust gases, then, $F /\left(\dot{m} V_{e}\right)$ is____________

Question ID - 155475 | SaraNextGen Top Answer

For a rocket engine, the velocity ratio $r$ is $V_{a} / V_{e},$ where $V_{a}$ is the vehicle velocity and $V_{e}$ is the exit velocity of the exhaust gases. Assume the flow to be optimally expanded through the nozzle. For $\boldsymbol{r}=2$, if $F$ is the thrust produced and $\dot{m}$ is the mass flow rate of exhaust gases, then, $F /\left(\dot{m} V_{e}\right)$ is____________