7 Quiz FLAPS

At a constant IAS in straight and level flight, if flaps are deployed the magnitude of the tip vortices will eventually:

• increase
• remain the same
• increase or decrease depending on the initial angle of attack
• decrease

A deployed slat will:

• decrease the boundary-layer energy and decrease the maximum negative pressure on the slat, so that Clmax is attained at a lower angle of attack
• increase the camber of the aerofoil and increase the effective angle of attack, so that Clmax is attained at a higher angle of attack
• increase the boundary-layer energy and move the maximum negative pressure from the wing completely to the slat, so that Clmax is attained at a higher angle of attack
• increase the boundary-layer energy and increase the maximum negative pressure on the wing, so that Clmax is attained at a higher angle of attack

The maximum angle of attack for the flaps-extended configuration when compared with the flaps-retracted configuration is:

• smaller or larger, dependent on the angle of flap deflection
• smaller
• larger
• unchanged

Which of the following statements is correct?

• Extension of the flaps will increase the maximum L/D ratio causing the minimum rate of descent to decrease.
• Extension of the flaps does not affect the minimum rate of descent because only the TAS has to be accounted.
• Spoiler extension decreases the stall speed and the minimum rate of descent but increases the minimum descent angle.
• Extension of the flaps reduces the stalling speed and decreases the maximum glide distance.

An efficient arrangement of the slats and/or leading-edge flaps on a swept-wing aeroplane is: wing roots (i) . . .. . .. . wing tips (ii) . . .. . .. .

• (i) L.E. Flaps; (ii) no devices
• (i) L.E. Flaps; (ii) slats
• (i) slats; (ii) L.E. flaps
• (i)slats; (ii) no devices

Where are Krueger flaps fitted?

• outboard on the wing leading edge
• outboard on the wing trailing edge
• inboard on the wing trailing edge
• inboard on the wing leading edge

To maintain straight and level flight when trailing-edge flaps are retracted the angle of attack must:

• be increased
• be decreased
• remain constant
• be increased or decreased dependent on the type of flap

When Fowler flaps are deployed on an aeroplane with a ‘T’ tailplane the pitching moments generated will be:

• nose-down
• nose-up
• will depend on the relative positions of the CP and the CG
• unchanged

When trailing-edge flaps are deployed the following occurs:

• Clmax increases and the critical angle of attack increases.
• The critical angle of attack remains constant but Clmax increases.
• The critical angle of attack decreases and Clmax increases.
• The critical angle of attack remains constant and the stalling speed increases.

The effect of deploying trailing-edge flaps is:

• increased minimum glide angle
• decreased minimum glide angle
• increased gliding endurance
• decreased sink rate