Last Updated On [03-11-2023]
In a particular rocket engine, helium propellant is heated to $6000 \mathrm{~K}$ and $95 \%$ of its total enthalpy is recovered as kinetic energy of the nozzle exhaust. Consider helium to be a calorically perfect gas with specific heat at constant pressure of $5200 \mathrm{~J} / \mathrm{kgK}$. The exhaust velocity for such a rocket for an optimum expansion is _____________$\mathrm{m} / \mathrm{s}$
Question ID - 155673 :- In a particular rocket engine, helium propellant is heated to $6000 \mathrm{~K}$ and $95 \%$ of its total enthalpy is recovered as kinetic energy of the nozzle exhaust. Consider helium to be a calorically perfect gas with specific heat at constant pressure of $5200 \mathrm{~J} / \mathrm{kgK}$. The exhaust velocity for such a rocket for an optimum expansion is _____________$\mathrm{m} / \mathrm{s}$
In a particular rocket engine, helium propellant is heated to $6000 \mathrm{~K}$ and $95 \%$ of its total enthalpy is recovered as kinetic energy of the nozzle exhaust. Consider helium to be a calorically perfect gas with specific heat at constant pressure of $5200 \mathrm{~J} / \mathrm{kgK}$. The exhaust velocity for such a rocket for an optimum expansion is _____________$\mathrm{m} / \mathrm{s}$
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An aircraft is flying level in the North direction at a velocity of $55 \mathrm{~m} / \mathrm{s}$ under cross wind from East to West of $5 \mathrm{~m} / \mathrm{s}$. For the given aircraft $\mathrm{C}_{\mathrm{n} \beta}=0.012 / \mathrm{deg}$ and $\mathrm{C}_{\mathrm{norr}}=-0.0072 / \mathrm{deg}$, where of is the
rudder deflection and $\beta$ is the side slip angle. The rudder deflection exerted by pilot is _____________degrees.
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