Cartes mémoires 081 POF Fragen (Seite 2 von 3)

Cartes-fiches	119
Langue	Deutsch
Catégorie	Technique
Niveau	Autres
Crée / Actualisé	05.06.2025 / 06.06.2025
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The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:

Positive

Maximum during cruise

Negative

Zero

The aerofoil polar is:

A graph of the relation between the lift coefficient and the angle of attack.

The relation between the horizontal and the vertical speed.

A graph of the relation between the lift coefficient and the drag coefficient.

A graph, in which the thickness of the wing aerofoil is given as a function of the chord.

The angle of attack of a propeller blade element is the angle between the blade element chord line and the:

TAS vector.

Propeller plane.

Propeller axis.

Resultant air speed vector.

The angle of climb of an aircraft is proportional to ________ and ________ as weight increases.

Excess power; decreases.

Excess thrust; increases.

Excess thrust; decreases.

Excess power; increases.

The contribution to the static directional stability of a straight wing with high aspect ratio and without dihedral:

Is always positive.

Is always negligible.

Becomes more positive as the aspect ratio increases.

Is always negative.

The descent angle of a given aeroplane in a steady wings level glide has a fixed value for a certain combination of: (ignore compressibility effects and assume zero thrust)

Mass and altitude.

Altitude and configuration.

Configuration and mass.

Configuration and angle of attack.

The effect of a ventral fin on the static stability of an aeroplane is as follows: (1 = longitudinal, 2 = lateral, 3 = directional)

1: no effect; 2: negative; 3: positive

1: no effect; 2: positive; 3: negative

1: positive; 2: negative; 3: negative

1: negative; 2: positive; 3: positive

The elevator deflection required for a given manoeuvre will be:

Larger for an aft CG position when compared to a forward position

Larger for a forward CG position when compared to an aft position

Larger at high IAS when compared to low IAS

The same at all speeds

The lateral axis of an aircraft is a line which passes through the ...

centre of pressure at right angles to the direction of the airflow

quarter chord point of the wing root at right angles to the longitudinal axis

centre of gravity, parallel to a line through the wing tip

wing tip

The manoeuvring speed VA, expressed as indicated airspeed, of a transport aeroplane:

Depends on aeroplane mass and pressure altitude

Is a constant value

Depends on aeroplane mass and is independent of pressure altitude

Is independent of aeroplane mass, but dependent on pressure altitude

The max aft position of the centre of gravity is amongst others limited by the ...

too small effect of the controls on the aeroplane.

maximum longitudinal stability of the aeroplane.

minimum value of the stick force per g.

maximum elevator deflection.

The maximum CL of a wing is ...

dependent on the surface area of the wing

increased by the use of high lift devices

constant and not affected by high lift devices

reduced when high lift devices are used

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

minimum lift/drag ratio.

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

CLmax.

speed for minimum power required.

The parameters that can be read from the "parabolic polar" curve of an aeroplane are the ...

aspect ratio of the wing and the induced drag coefficient.

min. glide angle and the parasite drag coefficient.

min. ROD and the induced drag.

induced drag and the parasite drag.

The shape of the gust load diagram is also determined by the following three vertical speeds in ft/s (clean configuration):

15, 56, 65

35, 55, 66

25, 55, 75

25, 50, 66

The stall speed in a 60° banked turn increases by the following factor:

2,00

1,41

1,07

1,30

Two identical aeroplanes A and B with the same mass are flying a steady level co-ordinated 20° bank turns. If the TAS of A is 130 kts and the TAS of B is 200 kts, the ...

lift coefficient of A is greater than that of B

load factor of A is greater than that of B

rate of turn of A is less than that of B

turn radius of A is greater than that of B

Upon which factor does wing loading during a level co-ordinated turn in smooth air depend?

Angle of bank.

Rate of turn.

TAS.

IAS.

What action is necessary to make an aircraft turn?

Yaw the aircraft

Roll the aircraft

Change the direction of thrust

Change the direction of lift

What happens to lateral stability when flaps are extended?

Lateral stability is unaffected, as the wings are symmetrical

Lateral stability is increased as lift is increased

Lateral stability is increased as the centre of pressure moves inboard

Lateral stability is decreased

What happens when trailing edge flaps are extended?

The critical AoA is constant, but CLmax increases

The critical AoA remains constant and stall speed increases

The critical AoA decreases and CLmax increases

The CLmax increases and the critical AoA increases

What is the approximate radius of a steady, level, co-ordinated turn with a bank angle of 30° and a TAS of 500 kt?

12 km.

24 km.

10 km.

7 km.

What is the correct relationship between the true airspeed for minimum sink rate (i) and minimum glide angle (ii), at a given altitude?

(i) is greater than (ii)

(i) can be greater than or less than (ii) depending on the type of aeroplane

(i) is less than (ii)

(i) is equal to (ii)

What is the correct relationship between the true airspeed for minimum sink rate and the true airspeed for minimum glide angle?

TAS for min sink rate is greater than TAS for min glide angle

It depends on the aircraft design

TAS for min sink rate is less than TAS for min glide angle

They are equal

What is the definition of mean aerodynamic chord (MAC)?

An average chord of an imaginary wing which has the same aerodynamic characteristics as the actual wing

The chord through the wing where the wing intersects the fuselage

A chord spanning from wing root to wing tip through the middle of the wing

The distance from the leading edge to the trailing edge of the wing root

What is the effect of elevator trim tab adjustment on the static longitudinal stability of an aeroplane?

Aeroplane nose down trim increases the static longitudinal stability

Aeroplane nose up trim increases the static longitudinal stability

No effect

Depends on the value of stick force/g

What may happen if the "ultimate load factor" is exceeded?

Elastic or temporary deformation only

No structural failure, only plastic or permanent deformation

Flutter

Structural failure

What wing shape or wing characteristic is the least sensitive to turbulence?

Swept wing

Wing with winglets

Wing with dihedral

Straight wing

When flaps are deployed at constant AoA, the lift coefficient will:

Decrease

Increase

Remain the same

Vary as the square of IAS

Which combination is applicable for structural strength in a gust in clean configuration?

50 ft/sec and Vc

66 ft/sec and Vd

65 ft/sec at all speeds

55 ft/sec and Vb

Which elevator deflection is required to maintain zero pitching moment when thrust is suddenly increased in a twin-engine jet aircraft with underwing engines?

Up

No elevator movement will be required because the thrust line of the engines remain unchanged

It depends on the position of the centre of gravity

Down

Which factor does NOT affect the angle of attack (AoA) during a standard rate turn?

TAS

Load factor

Weight

Wind

Which flight condition might result in a fully developed spin?

A steep spiral dive.

An inversed flight.

A partial stall with one wing low.

A basic uncoordinated stall.

Which of the following features increase static lateral stability?

Sweep back, under wing mounted engines, winglets.

High wing, sweep back, large and high vertical fin.

Low wing, dihedral, elliptical wing planform.

Fuselage mounted engines, dihedral, T-Tail.

Which of the following is a correct statement of gust factor applied in certification under JAR-25?

25 ft/sec at VB

50 ft/sec at VC

66 ft/sec at VD

55 ft/sec at VD

Which of the following statements about dihedral is correct?

Dihedral contributes to dynamic but not to static lateral stability.

Dihedral is necessary for the execution of slip-free turns.

Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane.

The "effective dihedral" of an aeroplane component means the contribution of that component to the static lateral stability.

Which of the following statements about the difference between Krueger flaps and slats is correct?

Slat will form a slot, deploying a Krueger flap does not

Krueger flap will increase critical angle of attack, deploying a slat does not

Krueger flap will form a slot, deploying a slat does not

Slat will increase critical angle of attack, deploying a Krueger flap does not

Which of the following statements about the spin is correct?

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

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

In the spin, airspeed continuously increases.

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

Which of the following statements about the stall of a straight wing aeroplane is correct?

Just before the stall the aeroplane will have a nose-down tendency.

The nose down effect is the result of increasing downwash, due to flow separation.

The horizontal tail will stall at a higher speed than the wing.

Buffeting is the result of flow separation on the tail plane.

Which of the following statements concerning control is correct?

Hydraulically powered control surfaces do not need mass balancing

On some aeroplanes, the servo tab also serves as a trim tab

In a differential aileron control system the control surfaces have a larger upward than downward maximum deflection

In general the maximum downward elevator deflection is larger than upward

081 POF Fragen

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