An aircraft has a mass of 5700 kg, the drag at best climb speed is 6675 N and the thrust available is 15.6 kN. The gradient of climb would be:
Climb Gradient % = (Thrust – Drag) / Weight x 100
Use ‘g’ = 10 m/s/s. Weight = 5700 x 10 = 57000 N
Climb Gradient % = (15600 – 6675) / 57000 x 100
Climb Gradient = 16%
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