20 - ATPL - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:
Question 20 - Principles of Flight - ATPL - Airline Transport Pilot license
0.74
1.71
2.49
1.49
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