Lernkartei 081 POF PT

Karten	62
Sprache	Deutsch
Kategorie	Technik
Stufe	Universität
Erstellt / Aktualisiert	22.06.2025 / 23.06.2025
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When the lift coefficient of a negatively cambered aerofoil section is zero, the pitching moment is:

Nose up (positive)

Zero

Maximum

Nose down (negative)

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

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

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

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

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

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

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

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

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

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

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 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

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

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

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

Which combination of design features is known to be responsible for deep stall?

Swept back wings and a T-tail

Straight wings and a T-tail

Swept back wings and wing mounted engines

Straight wings and aft fuselage mounted engines

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

Swept back wings and a T-tail

Straight wings and a T-tail

Swept back wings and wing mounted engines

Straight wings and aft fuselage mounted engines

At the stalling angle of attack the lift/drag ratio will be:

The same as at the optimum angle of attack

Higher than at the optimum angle of attack

Lower than at the optimum angle of attack

The angle of attack does not affect the lift/drag ratio

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

The same as at the optimum angle of attack

Higher than at the optimum angle of attack

Lower than at the optimum angle of attack

The angle of attack does not affect the lift/drag ratio

A wing stalling angle is:

Decreased in a high rate of turn

Increased in a high rate of turn

Unaffected by a turn

Decreased in any turn

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

Decreased in a high rate of turn

Increased in a high rate of turn

Unaffected by a turn

Decreased in any turn

During a spin recovery, the ...

control stick is moved sideways in the direction of the angle of bank

ailerons are held in the neutral position

control stick is moved sideways against the angle of bank

control stick is pulled to the most aft position

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

control stick is moved sideways in the direction of the angle of bank

ailerons are held in the neutral position

control stick is moved sideways against the angle of bank

control stick is pulled to the most aft position

The contribution of the wing to the static longitudinal stability of an aeroplane:

Depends on CG location relative to the wing aerodynamic centre

Depends on the wing location relative to the fuselage

Is positive if the wing has a positively cambered aerofoil section and the aerodynamic centre is ahead of the CG

Is always negative

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

Depends on CG location relative to the wing aerodynamic centre

Depends on the wing location relative to the fuselage

Is positive if the wing has a positively cambered aerofoil section and the aerodynamic centre is ahead of the CG

Is always negative

Longitudinal stability is given by the ...

horizontal tailplane

fin

ailerons

wing dihedral

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

horizontal tailplane

fin

ailerons

wing dihedral

The difference between the effects of slat and flap asymmetry is that:

Flap asymmetry causes a large rolling moment whereas slat asymmetry causes a large yawing moment

Flap asymmetry causes a large difference in CLmax whereas slat asymmetry causes a large rolling moment at any speed

Flap asymmetry causes a large rolling moment at any speed whereas slat asymmetry causes a large difference in CLmax

Flap asymmetry causes a large yawing moment whereas slat asymmetry causes a large rolling moment at any speed

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

Flap asymmetry causes a large rolling moment whereas slat asymmetry causes a large yawing moment

Flap asymmetry causes a large difference in CLmax whereas slat asymmetry causes a large rolling moment at any speed

Flap asymmetry causes a large rolling moment at any speed whereas slat asymmetry causes a large difference in CLmax

Flap asymmetry causes a large yawing moment whereas slat asymmetry causes a large rolling moment at any speed

When the right rudder pedal is depressed, the yaw-roll coupling gives a ...

rolling moment to the right

nose up pitching moment because the force is applied above the CG

rolling moment to the left

yawing moment but no rolling moment

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

rolling moment to the right

nose up pitching moment because the force is applied above the CG

rolling moment to the left

yawing moment but no rolling moment

Static directional stability is the:

Natural ability of an aeroplane to recover from a disturbance about the longitudinal axis

Tendency of an aeroplane to raise the low wing in a sideslip

Tendency of an aeroplane to recover from a disturbance about the lateral axis

Tendency of an aeroplane to recover from a skid with rudder free

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

Natural ability of an aeroplane to recover from a disturbance about the longitudinal axis

Tendency of an aeroplane to raise the low wing in a sideslip

Tendency of an aeroplane to recover from a disturbance about the lateral axis

Tendency of an aeroplane to recover from a skid with rudder free

A symmetrical fin will give a side force:

When the rudder is applied and when the aircraft yaws

Only when the aircraft yaws

Only when rudder is applied

With rudder neutral and no yaw

Tastatur-Befehle:

= drehen,

= vor-/rückwärts,

= scrollen

When the rudder is applied and when the aircraft yaws

Only when the aircraft yaws

Only when rudder is applied

With rudder neutral and no yaw

When spinning to the left, which parts of the aircraft are stalled?

Neither wing is stalled

Only the right wing is stalled

Only the left wing is stalled

Both wings are stalled

Neither wing is stalled

Only the right wing is stalled

Only the left wing is stalled

Both wings are stalled

Which of these statements about the gust load factor on an aeroplane are correct or incorrect?1. When the slope of the lift versus the AoA curve increases, the gust load factor increases.2. When the wing loading increases, the gust load factor increases.

1 correct; 2 incorrect

1 incorrect; 2 correct

1 correct; 2 correct

1 incorrect; 2 incorrect

1 correct; 2 incorrect

1 incorrect; 2 correct

1 correct; 2 correct

1 incorrect; 2 incorrect

For an aeroplane with one fixed value of VA the following applies. VA is …

just another symbol for the rough air speed

the maximum speed in smooth air

the speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor

the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW

just another symbol for the rough air speed

the maximum speed in smooth air

the speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor

the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW

An artificial stall warning device is normally set to warn …

3 seconds prior to stall

5–10 knots below stall

at stall

5–10 knots before stall

3 seconds prior to stall

5–10 knots below stall

at stall

5–10 knots before stall

Which of the following statements about stall speed is correct?

Decreasing the angle of sweep of the wing will decrease the stall speed

Increasing the anhedral of the wing will decrease the stall speed

Increasing the angle of sweep of the wing will decrease the stall speed

Use of a T-tail will decrease the stall speed

Decreasing the angle of sweep of the wing will decrease the stall speed

Increasing the anhedral of the wing will decrease the stall speed

Increasing the angle of sweep of the wing will decrease the stall speed

Use of a T-tail will decrease the stall speed

081 POF PT

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