Full extension of a Fowler flap will:

(b) increase the wing area and increase the camber

(a) increase the wing area only

When trailing-edge flaps are extended:

(a) the critical angle of attack decreases and the Clmax increases

(b) Clmax increases and the critical angle of attack increases

(c) Clmax increases and the critical angle of attack remains the same

(d) Vs increases and the critical angle of attack remains constant

The effect of deploying trailing-edge flaps is:

(a) increased minimum glide angle

(b) decreased minimum glide angle

(c) increased gliding endurance

If an aeroplane flies in ground effect the result will be:

(a) the lift increases and the drag decreases

(b) the effective angle of attack is decreased

(c) the induced angle of attack is increased

In straight and level flight at a constant mass, parasite drag is directly proportional to:

(d) the square of the angle of attack

Comparing Cl with Cd at a normal angle of attack:

(c) Cl is approximately equal to Cd

The lowest total drag in level flight is when:

(c) parasite drag is equal to induced drag

(d) parasite drag is twice the size of induced drag

(d) increases as the lift coefficient increases

(a) increases as the aspect ratio increases

(b) is not related to the lift coefficient

(c) increases in direct proportion to the size of the wing-tip vortices

The maximum L/D ratio is used to obtain:

(b) the maximum distance taken to glide from a specified altitude in still air

(a) the distance taken to climb to a specified altitude

(c) the glide distance from a specified altitude

(d) the minimum distance for the cruise

A high aspect ratio wing produces:

(a) an increased stalling speed

(d) less sensitivity to gust effects

The relationship between the induced drag and the aspect ratio is:

(a) a decrease in aspect ratio increases the induced drag

(c) induced drag = 1.3 times the aspect ratio

(d) increased aspect ratio increases the induced drag

Induced drag is created by the:

(b) spanwise flow pattern resulting in wing-tip vortices

(c) interference of the airstream between the wing and the fuselage

(d) separation of the boundary layer

If all other factors remain constant the effect that increased dynamic pressure has on total drag is:

(c) that it is only affected by the groundspeed

Which of the following reduces induced drag?

(b) elliptical lift distribution

A high aspect ratio wing:

(c) has greater structural strength than a low aspect ratio wing

(d) stalls at a higher angle than a low aspect ratio wing

In straight and level flight at a constant IAS, when flaps are lowered the induced drag:

(d) increases or decreases depending on aeroplane type

The effect that winglets have is that they:

(a) decrease the stalling speed

(b) increase static longitudinal stability

Ground effect could begin to be felt during the approach to land:

(b) at a height equal to one wingspan above the ground

(a) at a height equal to twice the wingspan above the ground

(c) when the angle of attack is increased

(d) at a height equal to half the wingspan above the ground

When an aeroplane enters ground effect the lift vector is inclined (i) . . . . . . . . ., which (ii) . . . . . . . . . . . the thrust required.

(d) (i) rearward (ii) increases

On entering ground effect:

(b) the power required is not affected

Deploying spoiler surfaces results in drag (i) . . . . . . . . . . and lift (ii) . . . . . . . . . .

(b) (i) increasing; (ii) decreasing

(a) (i) increasing; (ii) increasing

(c) (i) decreasing; (ii) increasing

(d) (i) decreasing; (ii) decreasing

Which of the following statements is correct regarding Vmd?

(b) The ratio of lift to drag is maximum.

(a) Parasite drag is greater than induced drag.

(c) The best glide range is achieved at this speed.

(d) It is the best endurance speed for a piston-engined aeroplane.

Which of the following statements regarding the stalling speed is correct?

(a) The stalling speed is decreased with a smaller angle of sweep.

(b) The stalling speed is increased with a smaller angle of sweep

(c) The stalling speed is decreased with T-tail.

(d) The stalling speed is decreased with increased anhedral.

Which of the following statements regarding the spin is correct?

(c) during spin recovery the ailerons should be in the neutral position

(a) in a spin the airspeed continually increases

(b) all aeroplanes are designed so that they can never spin

(d) an aeroplane is most likely to spin when the stall starts at the wing root

The effect on the stall that the downwash from a swept wing contacting a horizontal tail has is that it causes:

(a) a nose-up tendency and/or lack of elevator response

(c) increased sensitivity of elevator inputs

(d) a tendency to accelerate after the stall

The pitch-up effect of an aeroplane with swept wings in a stall is due to:

(d) the wing tip stalling first

(c) the wing root stalling first

During an erect spin recovery:

(a) the control column is moved to the most aft position

(b) the ailerons are held in the neutral position

(c) the control column is moved sideways in the opposite direction to the bank

(d) the control column is moved sideways in the same direction as the bank

Vortex generators on the upper surface of a wing will:

(b) decrease the intensity of the shockwave induced air separation

(a) increase the magnitude of the shockwave

(c) increase the critical Mach number

(d) decrease the spanwise flow at high Mach numbers

When an aerofoil stalls the lift (i) . . . . . . . . and the drag (ii) . . . . . . . . . . .

(d) (i) decreases; (ii) increases

(a) (i) decreases; (ii) decreases

(b) (i) remains constant; (ii) decreases

(c) (i) decreases; (ii) remains constant

The recovery procedure from a stall in a light single-engined aeroplane is:

(a) maximum power; stick forward roll neutral; correct for bank with rudder

(b) maximum power; stick neutral and forward, correct for bank with stick

(c) idle power; stick neutral; wait for normal nose-down tendency

(d) idle power; stick-roll neutral and forward

Where does flow separation commence at high angles of attack?

(a) upper surface towards the trailing edge

(b) upper surface towards the leading edge

(c) lower surface towards the trailing edge

(d) lower surface towards the leading edge

Vortex generators on the upper surface of the wing will:

(c) decrease the shock-wave-induced separation

(a) decrease the stalling speed by increasing the tangential velocity of the swept wing

(b) increase the effectiveness of the spoiler due to the increase of parasite drag

(d) decrease the interference drag of the trailing-edge flaps

The reason that swept-wing aeroplanes are more likely to deep stall is:

(d) The upper surface spanwise flow is from tip to root

CPD240 FINAL S/64

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Professional Development

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Practice Problem

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Supakrit Ariyapreecha

Used 1+ times

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(c) turn down

(d) move aft and then turn down

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CPD240 FINAL S/64

50 questions

In straight and level flight at a constant IAS if flap is selected, it will increase the:

After take-off in an aeroplane fitted with both slats and flaps the reason that it is customary to retract the flaps first is:

Extension of the Fowler-type trailing-edge flaps will produce:

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

The most efficient flap system is the:

The use of a slot at the leading edge of a wing enables the aeroplane to fly at a slower speed because:

Deploying a Fowler flap will cause it to:

Full extension of a Fowler flap will:

At a constant angle of attack, during flap retraction the aeroplane begins to:

When trailing-edge flaps are extended:

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