Last Updated On [03-11-2023]
A cruise missile with an ideal ramjet engine is flying at Mach 4.0 at an altitude where the ambient temperature is $100 \mathrm{~K}$. Considerratio of specific heats $=1.4$ and specific gas constant $\mathrm{R}=287 \mathrm{~J} / \mathrm{kgK}$. If the stagnation temperature in the combustion chamber is equal to $2310 K,$ the speed of the exhaust gases $(\mathrm{in} \mathrm{m} / \mathrm{s})$ is_______________________
Question ID - 155921 :- A cruise missile with an ideal ramjet engine is flying at Mach 4.0 at an altitude where the ambient temperature is $100 \mathrm{~K}$. Considerratio of specific heats $=1.4$ and specific gas constant $\mathrm{R}=287 \mathrm{~J} / \mathrm{kgK}$. If the stagnation temperature in the combustion chamber is equal to $2310 K,$ the speed of the exhaust gases $(\mathrm{in} \mathrm{m} / \mathrm{s})$ is_______________________
A cruise missile with an ideal ramjet engine is flying at Mach 4.0 at an altitude where the ambient temperature is $100 \mathrm{~K}$. Considerratio of specific heats $=1.4$ and specific gas constant $\mathrm{R}=287 \mathrm{~J} / \mathrm{kgK}$. If the stagnation temperature in the combustion chamber is equal to $2310 K,$ the speed of the exhaust gases $(\mathrm{in} \mathrm{m} / \mathrm{s})$ is_______________________
Next Question :
A gas turbine engine is operating under the following conditions:
Stagnation temperature at turbine inlet Stagnation pressure at the turbine inlet Static temperature at turbine exit Velocity at turbine exit Total-to-total efficiency of turbine $\mathrm{J} / \mathrm{k} \mathrm{K}$ $\gamma$ (ratio of specific heats) $\mathrm{C}_{\mathrm{P}}($ specific heat at constant pressure $)$ $1.147 \mathrm{~kJ} / \mathrm{kgK}$
The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to__________
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