CADA Exam 1

Identify the curved line marked H:

Induced Drag

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Parasite Drag

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Total Drag

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Angle of Attack

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Identify the point marked X:

Total Drag Location

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Minimum Parasite Drag

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Minimum Drag Speed

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Stalling Speed

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Identify the curved line located just above lines K and H:

Induced Drag

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Parasite Drag

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Total Drag

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Angle of Attack

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Identify the curved line marked Z:

Induced Drag

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Parasite Drag

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Total Drag

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Angle of Attack

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The point about which the wing pitching moment is independent of angle of attack is called:

the pitching centre

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the centre of gravity

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the centre of pressure

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the aerodynamic centre

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The angle of attack of a wing profile is defined as the angle between:

the undisturbed airflow and the chordline

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the local airflow and the mean camberline

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the local airflow and the chordline

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the undisturbed airflow and the mean camberline

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At a constant IAS, induced drag is affected by:

aircraft weight

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changes in thrust

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angle between chord line and longitudinal axis

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wing location

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Laminar flow has:

more friction than turbulent

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same friction as turbulent

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less friction than turbulent

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Which of the following wing planforms will be least affected by turbulence?

straight, high aspect ratio

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swept, low aspect ratio

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straight, moderate aspect ratio

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swept, high aspect ratio

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When Fowler flaps are deployed?

Only the area increases

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They move backwards then downwards

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They move downwards then backwards

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They move forwards

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With increasing angle of attack, the stagnation point will move (i) and the point of lowest pressure will move (ii).

(i) up, (ii) aft

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(i) down, (ii) forward

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(i) down, (ii) aft

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(i) up, (ii) forward

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On a cambered airfoil the zero lift angle of attack will be:

dependent on the wing aspect ratio

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positive

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negative

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zero

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High aspect ratio:

reduces parasite drag

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reduces induced drag

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increases stalling speed

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reduces manoeuvrability

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What is load factor?

lift multiplied by the total weight

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lift subtracted by the total weight

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lift divided by the total weight

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the total weight divided by the wing area

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Which statement is true, if during a level co-ordinated turn, the load factor was kept constant?

a decrease in airspeed result in an increase in radius

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an increase in airspeed results in an increase in radius

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an increase in airspeed results in a decrease in radius

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an increase in airspeed would result in the same radius

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If an aircraft with a gross weight of 2,000 kg was subjected to a 60° bank turn, what would the total load be?

1,000 kg

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2,000 kg

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4,000 kg

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12,000 kg

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Why is it necessary to increase bank elevator pressure to maintain altitude during a turn?

rudder deflection and slight aileron use throughout the turn

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due to the loss of the vertical component of lift

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due to the loss of the horizontal component of lift

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because the wing tip on the outside of the turn is travelling faster

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Which type of wing arrangement decreases the static lateral stability of an aeroplane?

Increased wing span

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Dihedral

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High wing

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Anhedral

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A propeller turns to the right, seen from behind. The torque effect in the take-off will:

pitch the aeroplane nose up

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pitch the aeroplane nose down

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roll the aeroplane to the right

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roll the aeroplane to the left

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On entering ground effect, maintaining flight at the same speed:

ground effect has no effect on power

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less power is required

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more power is required

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lift decreases

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What effect on induced drag does entering ground effect have:

Increase

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Decrease

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Remain the same

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Induced drag will increase, but profile drag will decrease

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Vortex generators:

take energy from the laminar flow to induce boundary layer separation

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use free stream flow to induce laminar flow

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prevent spanwise flow

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use free stream flow to increase energy in the turbulent boundary layer

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The primary purpose of wing spoilers is to decrease:

landing speed

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the lift of the wing

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the drag

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lift and drag

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What happens to lateral stability when flaps are extended?

Lateral stability is decreased

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Lateral stability is increased as lift is increased

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Lateral stability is unaffected, as the wings are symmetrical

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Lateral stability is increased as the centre of pressure moves inboard

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The maximum glide range of an aircraft will depend on wind and:

the ratio to lift to drag which varies according to angle of attack

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speed for minimum power required

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CL MAX

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minimum Lift/Drag ratio

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Which of the following will result in the maximum distance covered over the ground when gliding?

headwind

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tailwind

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increased weight

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decreased weight

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What phenomena causes induced drag?

Wing tip vortices

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Wing tanks

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The increased pressure at the leading edge

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The spanwise flow, inward below the wing and outward above

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On an airfoil the centre of pressure will be most forward:

On an airfoil the centre of pressure will be most forward:

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at the stalling angle

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just below the stalling angle

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just above the stalling angle

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When the undercarriage is lowered in flight:

form drag will increase and the aircrafts nose down pitching moment will be unchanged

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induced drag will increase and the aircrafts nose down pitching moment will increase

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form drag will increase and the aircrafts nose down pitching moment will increase

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induced drag will decrease and the aircrafts nose down pitching moment will increase

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The angle between the chord line of the wing and the longitudinal axis of the airplane is known as the angle of:

attack

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relative wind

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incidence

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dihedral

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is the ratio between the wing span and the root chord

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is the ratio between the wing span and the mean geometric chord

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is the ratio between the tip chord and the wing span

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is the ratio between chord and root chord

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Which of the following statements about the spin is correct?

In the spin, airspeed continuously increases

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An aeroplane is prone to spin when the stall starts at the wing root

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During spin recovery the ailerons should be kept in the neutral position

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Every aeroplane should be designed such that it can never enter a spin

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The stall speed increases, when? (all other factors of importance being constant)

weight decreases

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pulling out of a dive

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spoilers are retracted

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minor altitude changes occur eg. 0-10.000 ft

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How does stalling speed (IAS) vary with altitude?

It remains constant at lower altitudes but decreases at higher altitudes due to compressibility effects

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It remains constant

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It increases with increasing altitude, because the density decreases

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It remains constant at lower altitudes but increases at higher altitudes due to compressibility effects

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When washout is built into a wing:

there will be an increase in the wingtip vortices, leading to a decrease in downwash and a reduction in induced drag.

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there will be an increase in the angle of attack at the wingtip and hence greater lift can be produced leading to a decrease in the induced drag.

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the angle of incidence at the wingtip will be lower than that at the wing root, and the wingtip will reach the stalling angle after the wing root.

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the wingtip will have a greater angle of attack than the wing root, and the wing root will therefore stall before the wingtip.

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