Question 12. The engines of a propeller driven aircraft produce a maximum power that is independent of speed and has value equal to P kW at sea level. Considering only thrust

limited turns it is found that the aircraft's maximum power is required at sea level to turn at a load factor of 2.3 at 60 m s¹. Similarly maximum power is required to turn at a load factor of 3.5 at 40 m s¹ at sea level. If the aircraft turns at a speed of V m s¹ at sea level, what is the maximum load factor the turn can be performed at when only considering thrust limited turns? You should assume the drag equation is of the form Co=Co+KC [2+6 Marks] When submitting your worked solution to this question use the values P = 1600 kW and V = 55 m s.¹.