The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. An increase in angle of attack of 1 degree will increase CL by 0.09. A vertical up gust instantly changes the angle of attack by 5 degrees. The load factor will be:
Domanda 267, Principles of Flight - ATPL - Airline Transport Pilot license
| 1.09 |
| 2.0 |
| 2.13 |
| 3.18 |
