An aircraft is flying straight and level at constant altitude and constant speed. Which statement correctly describes the balance of forces?

Lift equals weight AND thrust equals drag Lift equals thrust AND weight equals drag Lift is greater than weight AND thrust equals drag Lift equals weight AND thrust is greater than drag

What is the chord of an aerofoil?

The distance from wingtip to wingtip The curvature of the upper wing surface The front-to-back length of the wing cross-section The maximum thickness of the wing profile

According to Bernoulli's principle, how does the curved upper surface of a wing contribute to lift?

Slower airflow over the upper surface creates higher pressure, pushing the wing up Faster airflow over the upper surface creates lower pressure, producing an upward force Air bouncing off the flat lower surface drives the wing upward The curved surface channels exhaust gases to generate thrust

A pilot gradually increases angle of attack while holding the same airspeed. What happens to lift as the critical angle of attack is exceeded?

Lift continues to increase indefinitely Lift remains constant but drag disappears Lift drops suddenly as the airflow separates from the upper wing surface Lift doubles because the angle deflects more air downward

Why do most modern airliners have swept-back wings?

Swept wings produce more lift at low speeds for takeoff Swept wings are lighter because they use less material Wing sweep raises the critical Mach number, allowing higher cruise speeds before compressibility effects begin Swept wings improve stability when landing in crosswinds

Which control surfaces are primarily responsible for controlling the roll of an aircraft?

Elevators, located on the horizontal tailplane Rudder, located on the vertical fin Ailerons, located on the outboard trailing edge of each wing Flaps, located on the inboard trailing edge of each wing

A pilot wants to raise the nose of the aircraft. Which control surface and which axis of rotation are involved?

Rudder controls pitch — rotation about the vertical axis Aileron controls pitch — rotation about the longitudinal axis Elevator controls pitch — rotation about the lateral (wingtip-to-wingtip) axis Spoiler controls pitch — rotation about the longitudinal axis

What is the purpose of trim tabs on an aircraft's control surfaces?

Trim tabs act as speed brakes to slow the aircraft during descent Trim tabs hold the aircraft in balanced flight without the pilot exerting continuous force on the controls Trim tabs increase the total lift generated by the wing Trim tabs divert thrust to control yaw at low speed

An airliner is in level flight at 1g. During an abrupt pull-up manoeuvre, the load factor reaches 2.5g. What does this mean?

The aircraft is flying 2.5 times faster than its normal cruise speed The lift force equals 2.5 times the aircraft's weight The engine is producing 2.5 times its normal thrust The drag force equals 2.5 times the thrust

Which type of loads are aircraft wings specifically designed to flex under, in order to reduce structural stress?

Normal level-flight loads that act continuously Landing loads transmitted from the undercarriage Manoeuvre loads produced during intentional pull-up or banking Gust loads — sudden changes in airspeed or direction caused by turbulence

On a V-n diagram, what does the 'never-exceed speed' (VNE) represent?

The speed at which the aircraft must rotate for takeoff The maximum airspeed beyond which structural failure or loss of control is possible The speed below which the aircraft will stall at 1g The design limit load factor speed at maximum weight

If a wing's design limit load is 3.8g, what is the design ultimate load the structure must withstand without breaking?

3.8g (same as the design limit load) 4.5g (approximately 3.8g + 0.7g margin) 5.7g (1.5 × 3.8g) 7.6g (2.0 × 3.8g)