Cartes mémoires 081 POF PT (Seite 2 von 2)

Cartes-fiches	62
Langue	Deutsch
Catégorie	Technique
Niveau	Université
Crée / Actualisé	22.06.2025 / 23.06.2025
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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

Maximum elevator deflection

Minimum value of the stick force per g

An aircraft flying at 150kts EAS at 10,000ft compared to the same aircraft flying at the same EAS at sea level will have:

A lower TAS

The same angle of attack

A smaller angle of attack

A larger angle of attack

What procedure is the one if you have remaining ice on the aircraft at final approach for landing?

Less flap setting and a higher Vldg in order to get the greatest possible marginal to wing and tail stall

Flaps full and a higher Vldg in order to get the greatest possible marginal to wing and tail stall

Less flap setting and normal Vldg in order to get the greatest possible marginal to wing and tail stall

Flaps full and normal Vldg in order to get the greatest possible marginal to wing and tail stall

A few millimeters of rough ice on the leading edge of a wing:

Can reduce the maximum lift coefficient by 50%

Will marginally increase the lift coefficient

Will normally have no effect on the lift coefficient

Can reduce the maximum lift coefficient by 30%

The nose up or nose down orientation of an aircraft relative to the horizon is known as the ...

attitude of the aircraft

angle of attack

angle between the relative airflow and the chord line of the wing

angle of incidence

The lift coefficient versus angle of attack curve of a positively cambered aerofoil section intersects the horizontal axis of the graph:

To the right of the origin

At the origin

To the left of the origin

Nowhere

Assuming constant IAS, when an AC leaves ground effect:

Induced drag decreases

The induced AoA decreases

The effective AoA decreases

The effective AoA increases

When the lift coefficient of a negatively cambered aerofoil section is zero, the pitching moment is:

Nose up (positive)

Zero

Maximum

Nose down (negative)

Lift is a function of:

Velocity, wing shape, wing area and CL

Velocity, density, gross wing area and CD

Velocity, wing area, CL and density

Velocity, density, wing shape and lift coefficient

In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will ...

increase

decrease

increase or decrease depending on type of flap

remain constant

The point, where the aerodynamic lift acts on a wing is the ...

suction point of the wing

point of maximum thickness of the wing

CG location

centre of pressure

Lift is generated when:

a symmetrical aerofoil is placed in a high velocity air stream at zero angle of attack

a certain mass of air is accelerated in its flow direction

a certain mass of air is retarded

the flow direction of a certain mass of air is changed

When roll spoilers are extended, the part of the wing on which they are mounted...

is forced downwards as a reaction to the increased drag

experiences a reduction in lift which generates the desired rolling moment. In addition there is a local increase in drag which suppresses adverse yaw

experiences extra drag which generates a yawing moment. The speed difference between both wings generates the desired rolling moment

stalls. This causes a difference in lift between both wings, which generates the desired rolling moment

The increased upwash experienced at the leading edge of a wing when trailing edge flaps are lowered causes:

An increase in the AoA

A rearward movement of the CG

A forward movement of the CP

A reduction in CL max

The purpose of fillet on a wing is to ...

reduce interference drag

increase lift

increase skin friction drag

reduce induced drag

Under icing conditions the risk of flow separation on the tail surface:

Increases with increasing speed and increasing flap deflection

Decreases with increasing speed and increasing flap deflection

Is non-existing due to aerodynamic safety design features

Is non existing due to the smaller angle of incidence compared to the main wing

Which statement about an aeroplane entering ground effect is correct? 1. The downwash angle decreases. 2. The induced AoA decreases.

1. is correct; 2. is incorrect

1. is incorrect; 2. is incorrect

1. is correct; 2. is correct

1. is incorrect; 2. is correct

For a given angle of attack, a swept wing will have ...

reduced lateral stability than an equivalent straight one

a lower lift coefficient than an equivalent straight one

the same lift coefficient than an equivalent straight one

the same lateral stability than an equivalent straight one

In order to generate the same amount of lift as altitude is increased, an aeroplane must be flown at ...

A higher TAS for any given AoA

The same TAS regardless of AoA

A lower TAS for any given AoA

A lower TAS and a lower AoA

A line from the centre of curvature of the leading edge of a cambered aerofoil to the trailing edge, equidistant from the top and bottom surfaces is the ...

mean camber line

upper camber line

chord line

MAC

What will happen in ground effect?

A significant increase in thrust required

An increase in strength of the wing tip vortices

The induced AoA and induced drag decreases

The wing downwash on the tail surfaces increases

What statement is correct about the shape of an airfoil?

The ratio between the camber line and the chord is called the camber of the airfoil

The distance between the airfoil upper surface and the chord line is called camber

The camber means the curvature of the upper surface

The chord is defined as the distance between the leading edge and trailing edge of the airfoil

081 POF PT

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