Given that the characteristics of a three engine turbojet aeroplane are as follows: Thrust = 50 000 Newton / Engine, g = 10 m/sē, Drag = 72 569 N, Minimum gross gradient (2nd segment) = 2.7% SIN(Angle of climb) = (Thrust- Drag) / Weight. The maximum take-off mass under 2nd segment conditions is:
The only way i get the answer that the data base gives is by assuming one engine is out...but at no point in the question does it say that it is.
Last edited by squall1984; 28th Aug 2013 at 16:02.