The thrust of a rocket engine is defined by:

1- mass flow x exhaust gases velocity

2- engine's mass flow x aircraft velocity

3- the force as a result of a certain mass flow acceleration

Amongst the statements below, choose the correct answer...

Which of the following statements is true?

1 A turbofan CAN NOT fly to a supersonic regime.

2 Bypass ratio of a military turbofan is usually SMALLER than that of a civil turbofan.

3 A turbofan increases the Thrust and Efficiency WHILE reducing the engine noise.

About the combustion chamber:

1 A combustion chamber can be cooled by introducing air through the walls of it.

2 About 25% of the air intake of a jet engine is used to cool the combustion chamber.

3 The flame temperature is lower than the temperature of the walls of the combustion chamber.

Talking about rocket and turbojet engines...

1 a jet engine needs the oxidiser, that comes from outside

2 a rocket engine can be operated under the water

3 a rocket engine needs no atmosphere outside to operate

When a compressor works nominally, then

The phugoid motion preserves the pitching angle of the airplane throughout the oscillation

Which of the following wing parameters influence lateral stability?

A very effective horizontal stabiliser is also good for manoeuvrability and fast response.