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:
1 deg increase = 0.079 x 2 = 0.155
NEW CL 0.35 + 0.155 = 0.508
/ OLD CL 0.35 = 1.451