301 - ATPL - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. An increase in angle of attack of 1 degree would increase CL by 0.079. If a vertical gust instantly changes the angle of attack by 2 degrees, the load factor will be:
Question 301 - Principles of Flight - ATPL - Airline Transport Pilot license
0.9
1.45
1.9
0.45
Training tests and timed exam simulations ATPL - Airline Transport Pilot license
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