149) In what way is the longitudinal stability affected by the
degree of positive camber of the aerofoil?
A Positive, because the centre of pressure shifts rearward at
increasing angle of attack.
B Negative, because the lift vector rotates forward at
increasing angle of attack.
C Positive, because the lift vector rotates backward at
increasing angle of attack.
D No effect, because camber of the aerofoil produces a
constant pitch down moment coefficient, independent of
angle of attack.
148) The lift coefficient (CL) of an aeroplane in steady
horizontal flight is 0.35. Increase in angle of attack of 1
degree will increase CL by 0.079. A vertical up gust
instantly changes the angle of attack by 2 degrees. The
load factor will be :
A 1.9
B 1.45
C 0.9
D 0.45
Non so se in UK le domande sono diverse, ma le domande su cui studio sono di questo genere, e ne ho 25 Mb
Ciao
Andrea