ATPL Principles of Flight and Aerodynamics 2

Question 1

Positive static stability in an aircraft means that after a disturbance, the aircraft will:

Accepted Answer

Initially develop restoring forces toward the original attitude

Answer

Continue to diverge from its original attitude

Answer

Remain fixed in the disturbed attitude

Answer

Oscillate with increasing amplitude

Question 2

Dutch roll is a lateral-directional oscillation that involves coupling of:

Accepted Answer

Roll and yaw axes

Answer

Pitch and roll axes

Answer

Pitch and yaw axes

Answer

All three axes in equal measure

Question 3

Wing dihedral angle primarily provides stability about the:

Accepted Answer

Longitudinal axis (lateral/roll stability)

Answer

Lateral axis (pitch stability)

Answer

Vertical axis (directional/yaw stability)

Answer

All three axes equally

Question 4

Adverse yaw in conventional aircraft is caused by:

Accepted Answer

Differential aileron drag during a roll input

Answer

Differential engine thrust during a turn

Answer

Rudder deflection creating a secondary rolling moment

Answer

Asymmetric flap extension

Question 5

The primary purpose of a yaw damper in a modern transport jet is to:

Accepted Answer

Automatically damp Dutch roll oscillations with small rudder inputs

Answer

Increase yaw stability during crosswind landings automatically

Answer

Prevent rudder input reversal during high-speed flight

Answer

Coordinate turns by applying rudder proportional to bank angle

Question 6

A neutrally stable aircraft, when disturbed from its trimmed attitude and released, will:

Accepted Answer

Maintain the new disturbed attitude indefinitely

Answer

Return to its original trimmed attitude

Answer

Continue to diverge from its original attitude

Answer

Oscillate symmetrically about its original attitude with constant amplitude

Question 7

The aerodynamic center of an airfoil is the point about which the pitching moment coefficient:

Accepted Answer

Remains approximately constant with changes in angle of attack

Answer

Is always zero for all angles of attack

Answer

Changes significantly with angle of attack

Answer

Equals the center of pressure at low speeds