M 11.1 - Theory of Flight - Airplane Aerodynamics and Flight

As a Subsonic aircraft speeds - up, its center of pressure

• moves forward

• moves aft

• is unaffected

Answer explanation

Assuming that the aircraft is to remain at constant altitude, it must reduce its angle of attach as it speeds - up. This alone will move the CofP rearwards, in accordance with the subsonic angle of attache change theory.

A split flap, when deployed

• increases drag with little lift coefficient increase, from intermediate to fully down

• is used only on high speed aircraft

• increases lift without a corresponding increase in drag

A plain flap

• is attached to the leading edge of the wing

• forms part of the lower trailing edge

• doesn't increase the wing area on deployment

Sweepback will

• increase lateral stability

• not affect lateral stability

• decrease lateral stability

Krueger flaps are on

• the leading edge

• the trailing edge

• either the leading or trailing edge

Leading edge flaps

• decrease stalling angle of the wing

• do not change the stalling angle

• increase stalling angle of the wing

Vortex generators are fitted to

• move transition point forwards

• move transition point rearwards

• advance the onset of flow separation

Instability giving roll and yaw

• is longitudinal stability

• is lateral stability

• is dutch roll

If an aircraft is yawing left, the trim tab on the rudder would be positioned

• to the left, moving the rudder right

• to the center

• to the right, moving the rudder left

Induced drag curve characteristics of a slender delta wing are such that there is

• an increase in gradient with wing speed

• decrease in gradient with wing speed

• no change in gradient with wing speed