Q4. Consider an aircraft flying in straight and level flight with total wing area 110 m², wing

loading 2600 N/m² and a drag polar of 0.02 +0.06C2, at sea level. The aircraft engines can

generate up to 1.8 times the thrust needed to maintain straight and level flight at 175 m/s.

Calculate the climb rate that this aircraft could achieve.

[10 marks]

Q5. Summarise the ways in which the trim of an aircraft can be controlled by a pilot.

[6 marks]

Q6. Define the aerodynamic centre and why it's a useful point on an aircraft for analysing

aerodynamic forces.

[4 marks]