Aturbojet is at an altitude of 35,000 ft traveling at a mach number of 0.7. it has an inlet area of 8 ft^2 and an exit area of 5 ft^2. the exit velocity is 1700 ft/s and the exit pressure is 700 lb/ft2. the fuel-to-air ratio (by mass) is 0.05.
a. ignoring the mass of the fuel, calculate the thrust produced by the turbojet.
b. recalculate the thrust of the turbojet but do not ignore the mass of the fuel.
c. what is the percent error in ignoring the mass of the fuel when calculating the thrust?
d. the turbojet has a diffuser after the engine inlet. at the end of the diffuser, the mach number is 0.2. calculate the pressure at the end of the diffuser. (hint: the flow is isentropic so the total pressure will be constant)
e. estimate the thrust of this turbojet engine at sea level.