When an aeroplane performs a straight steady climb with a 20% climb gradient, the load
factor is equal to:
0.83
1
0.98
1.02
load factor = L/W
L = W . cos angle
angle = 20° = 0,2
L/W = cos 0,2
L/W = 0,9396 ...
-> there is no right answer ?? (0,98 is marked as a right one)