Lernkartei 081 POF PT (Seite 1 von 2)

Karten	62
Sprache	Deutsch
Kategorie	Technik
Stufe	Universität
Erstellt / Aktualisiert	22.06.2025 / 23.06.2025
Weblink	https://card2brain.ch/box/20250622_081_pof_pt
Einbinden	<iframe src="https://card2brain.ch/box/20250622_081_pof_pt/embed" width="780" height="150" scrolling="no" frameborder="0"></iframe>

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

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

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

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

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

Longitudinal stability is given by the ...

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

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

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

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

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

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

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

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

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

Which of the following increases the tendency for “Dutch roll”?

Increased anhedral

Decreased dihedral

Increased static lateral stability

Increased keel surface aft of the CG

The speed for minimum sink rate in a glide, compared to the speed for maximum distance Vmd, is:

Slower than Vmd

Faster than Vmd

Not related to Vmd

Equal to Vmd

Which three aerodynamic means decrease manoeuvring stick forces?

Spring tab – horn balance – bobweight

Servo tab – trim tab – balance tab

Spring tab – trim tab – mass balancing weight

Servo tab – horn balance – spring tab

The aerodynamic contribution to the static longitudinal stability of nacelles of aft fuselage-mounted engines is:

Positive

Negative

Zero

Maximum during cruise

What happens when the CG is moving forward?

Vs decreases, stall angle decreases

Vs decreases, stall angle remains constant

Vs increases, stall angle remains constant

Vs increases, stall angle increases

The aerodynamic centre of the wing is the point where…

The lateral axis intersects the centre of gravity

Pitching moment coefficient does not vary with angle of attack

Aerodynamic forces are constant

Change of lift due to angle of attack is constant

In a turn, the stalling speed will be:

Higher than in level flight but at a lower angle of attack

Less than in a level flight

Higher than in a level flight and at the same angle of attack

The same as in level flight

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

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

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

wing tip

Which of the following might be symptoms of an approaching spin?

Aerodynamic buffet, stall

Lateral instability, autorotation

Pitch up or pitch down (swept wing)

All of the answers are correct

The turn co-ordinator shows a right turn. The slip co-ordinator indicates left of the neutral position. What is the action to co-ordinate the turn?

More right rudder input

More right bank

More left bank

Less right bank

If an aeroplane has poor longitudinal stability, what can be done to increase it?

Reduce in keel surface area

Increase stabilizer surface area

Install a yaw damper

Increase elevator range of movement

Static lateral stability should not be too small because:

After a disturbance around the longitudinal axis the aeroplane would show a too strong tendency to return to the original attitude

The aeroplane would show a too strong tendency to spiral dive

The stick force per g would become unacceptably small

The aeroplane would show a too strong tendency to Dutch roll

During landing of a low-wing jet aeroplane, the maximum elevator up deflection is normally required when the flaps are:

Up and the CG is full aft

Full down and the CG is full aft

Full down and the CG is full forward

Up and the CG is full forward

The change in downwash along a wing without taper:

Reduces the adverse yaw effect in roll.

Increases the load factor at the wing tip.

Causes the stall to occur at the root first.

Reduces damping in roll.

A horn balance in a control system has the following purpose to ...

prevent flutter.

decrease stick forces.

decrease the effective longitudinal dihedral of the aeroplane.

obtain mass balancing.

When the rudder is moved to the right, the force acting on the fin gives a ...

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

rolling moment to the left.

rolling moment to the right.

yawing moment but no rolling moment.

When a pilot makes a turn in horizontal flight, the stall speed:

Increases with flap extension.

Decreases with increasing bank angle.

Increases with the load factor squared.

Increases with the square root of load factor.

A boundary layer fence on a swept wing will:

Improve the low speed characteristics

Improve the high speed characteristics

Increase the critical Mach number

Improve the lift coefficient of the trailing edge flap

A laminar boundary layer is a layer in which:

The vortices are weak

The velocity is constant

The temperature varies constantly

No velocity components exist normal to the surface

The lift and drag forces, acting on a wing cross section:

Vary linearly with the angle of attack

Depend on the pressure distribution about the wing cross section

Are normal to each other at just one angle of attack

Are proportional to each other, independent of angle of attack

Which kind of boundary layer has the strongest change in velocity close to the surface?

No difference

Laminar boundary layer

Turbulent boundary layer

Transition boundary layer

Superstall is a ...

Unstable stalled condition at a variable pitch attitude, with straight wings

Stable stalled condition at a constant pitch attitude, with rectangular wings

Stable stalled condition at a constant pitch attitude, with swept wings

Unstable stalled condition at a variable pitch attitude, with swept wings

If the total sum of moments about one of its axis is not zero, an aeroplane would:

Be difficult to control

Fly a path with a constant curvature

Experience an angular acceleration about that axis

Not be affected because the situation is normal

As a result of gyroscopic precession, it can be said that:

Any yawing around the normal axis results in a pitching moment

Any pitching around the longitudinal axis results in a yawing moment

Any pitching around the lateral axis results in a rolling moment

Any rolling around the longitudinal axis results in a pitching moment

The units of a turning moment are:

Joule

Kilogram

Rate / second

Newton x meters

081 POF PT

Lernkarteien erstellen oder kopieren

Lernkarteien erstellen oder kopieren

Melde dich an, um alle Karten zu sehen.

SWITCHaai

Office 365

Edulog

Apple ID

Google