For an adiabatic and reversible, converging-diverging nozzle, operating in vacuum:Group of answer choicesSpecific thrust always increases with increasing area ratioSpecific thrust is maximised at a particular, finite area ratioA purely-converging nozzle will produce the same thrust as a converging-diverging nozzle, irrespective of area ratioThe Mach number at the throat will be moderately supersonic

The momentum thrust of a choked purely-converging nozzle of fixed area, fed by a reservoir of fixed composition and temperature:Group of answer choicesIncreases with increasing reservoir pressureRemains constant with decreasing backpressureAll of the aboveNone of the above

In turbojets with purely converging propelling nozzles, part of the thrust is also generated by the pressure difference:Group of answer choicesOnly when the flow is chokedBoth a and cWhether the flow is choked or notWhen the nozzle is operated overexpanded

During the isentropic expansion of a flow in an ideal choked diverging nozzle:Group of answer choicesThe static pressure is decreasing as the velocity and Mach number decreasesThe static pressure remains constantThe total enthalpy and the static pressure are dropping as the Mach number increasesThe static pressure is decreasing as the velocity and Mach number increases

Which of the following is true about a nozzle?1 pointNozzles are not adiabatic. The area at the exit is greater than the area at the entrance of a nozzle. The velocity of the fluid at the entrance is larger than the velocity of the fluid at the exit of a nozzle. There is a change in pressure from the inlet to the outlet of the nozzle.

.Question 12Which of the following is true about a nozzle?1 pointNozzles are not adiabatic. The area at the exit is greater than the area at the entrance of a nozzle. The velocity of the fluid at the entrance is larger than the velocity of the fluid at the exit of a nozzle. There is a change in pressure from the inlet to the outlet of the nozzle.