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Consider a twin-engined aircraft with the following specification:
- Basic aerodynamic performance CD0 = 0.0168; k = 1.20; AR = 8.6;
- Take-off flap configuration: CLmax = 2.00; CD increment = 0.0130;
- Air speed during 2nd segment climb, V2 = 1.15 x stall speed
- Throttle setting = 75%
- Minimum climb gradient = 1.5%
Answer the following three questions in turn:
Q1 What is the value CL during 2nd segment climb, to 3 d.p.?
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