JAA ATPL Question 5017

0 Replies
2,025 votes ยท 22 hours left
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42, increase in angle of attack of 1 degree increases CL by is 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be : #atpl #jaa #dgca #pilot #aviation
Some text some message..