List of top Propulsion Questions on Turbofan Thrust

An ideal turbofan with a bypass ratio of 5 has core mass flow rate, \( \dot{m}_a,c = 100 \, {kg/s} \). The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to \( \dot{m}_a,c \), the static specific thrust (\( \frac{T}{\dot{m}_a,c} \)) developed by the engine is _________ Ns/kg (rounded off to the nearest integer).

An ideal turbofan with a bypass ratio of 5 has core mass flow rate, \( \dot{m}_a,c = 100 \, {kg/s} \). The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to \( \dot{m}_a,c \), the static specific thrust (\( \frac{T}{\dot{m}_a,c} \)) developed by the engine is \_\_\_\_\_\_\_ Ns/kg (rounded off to the nearest integer).
An ideal turbofan with a bypass ratio of 5 has core mass flow rate, \( \dot{m}_a,c = 100 \, {kg/s} \). The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to \( \dot{m}_a,c \), the static specific thrust (\( \frac{T}{\dot{m}_a,c} \)) developed by the engine is \_\_\_\_\_\_\_ Ns/kg (rounded off to the nearest integer).
An ideal turbofan with a bypass ratio of 5 has core mass flow rate, \( \dot{m}_a,c = 100 \, {kg/s} \). The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to \( \dot{m}_a,c \), the static specific thrust (\( \frac{T}{\dot{m}_a,c} \)) developed by the engine is \_\_\_\_\_\_\_ Ns/kg (rounded off to the nearest integer).

An aircraft with a turbojet engine is flying with \(V_0=250\ \text{m s}^{-1}\) at an altitude where \(\rho=1\ \text{kg m}^{-3}\). The inlet area is \(A_0=1\ \text{m}^2\). The average exhaust-gas speed at the nozzle exit, with respect to the aircraft, is \(V_{e,\text{rel}}=550\ \text{m s}^{-1}\). The exit pressure equals ambient and fuel–air ratio is negligible. Find the uninstalled thrust (rounded to the nearest integer).

From the options given, select all that are true for turbofan engines with afterburners.