Set of flashcards 081 POF Fragen (Page 3 of 3)

Flashcards	119
Language	Deutsch
Category	Technology
Level	Other
Created / Updated	05.06.2025 / 06.06.2025
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Which of the following statements is correct?

An aeroplane with an excessive static directional stability in relation to the static lateral stability of the aircraft can develop a so called 'Dutch roll'.

The effects of static stability around the lateral and the directional axis is independent of each other.

An aeroplane with an excessive static directional stability in relation to the static longitudinal stability of the aircraft can develop a so called 'Dutch roll'.

An aeroplane with an excessive static directional stability in relation to the static lateral stability of the aircraft can develop a spiral instability.

Which of these statements concerning flight in turbulence is correct?

VB is the recommended turbulence penetration air speed

The load factor in turbulence may fluctuate above and below 1, but will not become negative

In severe turbulence speed should be reduced to approximately 1.2 VS

VRA is the recommended turbulence penetration air speed

Which statement concerning sweepback is correct?

Sweepback provides a positive contribution to static lateral stability.

Sweepback is mainly intended to increase static directional stability.

A disadvantage of sweepback is that it decreases MCRIT.

Sweepback increases speed stability at Mach numbers above MCRIT.

Which statement is correct about a spring tab?

At high IAS it behaves like a servo tab

At high IAS it behaves like a fixed extension of the elevator

Its main purpose is to increase stick force per g

At low IAS it behaves like a servo tab

Which three aerodynamic means decrease manoeuvring stick forces?

Servo tab – trim tab – balance tab

Spring tab – trim tab – mass balancing weight

Servo tab – horn balance – spring tab

Spring tab – horn balance – bobweight

Why does a transport aircraft with powered controls use a horizontal stabiliser trim?

Trim tabs are not effective enough

Trim tabs would increase Mcrit

Overly complex mechanism

Pilot input is not subject to aerodynamic control forces

With increasing altitude and constant IAS, the static lateral stability (i) and the dynamic lateral/directional stability (ii) of an aeroplane with swept back wing will:

(i) increase; (ii) increase

(i) decrease; (ii) increase

(i) increase; (ii) decrease

(i) decrease; (ii) decrease

You are flying in horizontal flight with a CL of 0.42. An increase in AoA by 1° increases CL by 0.1. A gust increases AoA by 3°. What load factor results from the gust?

1.26

0.30

1.71

0.72

Floating due to ground effect during an approach to land will occur:

When the height is less than twice the length of the wing span above the surface

At a speed approaching the stall

When the height is less than half of the length of the wing span above the surface

When a higher than normal AoA is used

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

Decrease

Vary as the square of IAS

Increase

Remain the same

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 …

upper camber line

chord line

MAC

mean camber line

With a decrease in angle of attack:

the stagnation point moves forward

induced drag will increase

form drag will increase

the separation point moves forward

What statement is correct about the shape of an airfoil?

The camber means the curvature of the upper surface

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

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

An increase of temperature of the stream at constant value of V will:

not affect the mass flow

increase the mass flow

increase the mass flow when the tube is divergent in the direction of the flow

decrease the mass flow

An aeroplane maintains straight and level flight while the speed is doubled. The change in lift coefficient will be:

x 2.0

x 0.25

x 4.0

x 0.5

The purpose of streamlining is to …

reduce interference drag

reduce form drag

increase lift

reduce skin friction drag

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 smaller angle of attack

The same angle of attack

A lower TAS

A larger angle of attack

Assuming constant IAS, when an AC leaves ground effect:

The effective AoA increases

Induced drag decreases

The induced AoA decreases

The effective AoA decreases

Assuming zero wing twist, the wing planform that gives the highest local lift coefficient at the wing root is:

Tapered

Rectangular

Elliptical

Swept back

Which statement about an aeroplane leaving ground effect at constant AoA is correct?1. The lift coefficient CL increases.2. The induced drag coefficient CDI increases.

1. is correct; 2. is correct

1. is correct; 2. is incorrect

1. is incorrect; 2. is correct

1. is incorrect; 2. is incorrect

What will happen in ground effect?

A significant increase in thrust required

The wing downwash on the tail surfaces increases

An increase in strength of the wing tip vortices

The induced AoA and induced drag decreases

What must happen to the CL when flaps are deployed while maintaining a constant IAS in straight and level flight?

Remain constant

Increase then decrease

Decrease

Increase

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

a lower lift coefficient than an equivalent straight one

the same lift coefficient than an equivalent straight one

reduced lateral stability than an equivalent straight one

the same lateral stability than an equivalent straight one

The construction feature of a wing called "Geometric Wash Out" is:

A decrease in the angle of incidence from root to tip

An increase in the angle of incidence from root to tip

An increase of camber from root to tip

A decrease of camber from root to tip

The induced angle of attack is the result of:

A large local angle of attack in a two dimensional flow

Change in direction of flow due to the effective angle of attack

Downwash due to flow separation

Downwash due to tip vortices

The coefficient of induced drag (CDi) is proportional to the ratio of:

CL² and S (wing surface)

CL and b (wing span)

CL² and AR

CL and CD

In which phase of the takeoff is the aerodynamic effect of ice located on the wing leading edge most critical?

All phases of the takeoff are equally critical

The last part of the rotation

During climb with all engines operating

The takeoff run

Parasite drag is,

directly proportional to indicated airspeed squared

directly proportional to the square root of the indicated airspeed

inverse proportional to true airspeed

directly proportional to ground speed squared

Which statement is correct?

Flap extension has no effect on the minimum rate of descent as this is only affected by TAS

Flap extension reduces the stallspeed, which increases the maximum glide distance

Flap extension reduces the maximum lift/drag ratio thus reducing the minimum rate of descent

Spoiler extension increases the stall speed, the minimum rate of descent and the minimum angle of descent

If the increased downwash at the tail plane due to lowering trailing edge flaps is considered in isolation:

A nose down pitching moment will be generated

A nose up pitching moment will be generated

The direction of the pitch change will depend on the initial direction of the tail load

Tail plane angle of attack will be decreased causing a nose up pitching moment

The induced drag coefficient, CDi is proportional with:

Square root (CL)

CLmax

CL2

CL

The purpose of fillet on a wing is to …

reduce interference drag

increase skin friction drag

increase lift

reduce induced drag

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 correct

1. is incorrect; 2. is incorrect

1. is correct; 2. is incorrect

1. is incorrect; 2. is correct

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

increase

remain constant

decrease

increase or decrease depending on type of flap

Given an aeroplane in steady, straight and level flight at low speed. Considering the effects of centre of gravity location and thrust, the highest value of wing lift occurs at:

Aft CG and take-off thrust

Aft CG and idle thrust

Forward CG and idle thrust

Forward CG and take-off thrust

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

Vary linearly with the angle of attack

Are proportional to each other, independent of angle of attack

Are normal to each other at just one angle of attack

Depend on the pressure distribution about the wing cross section

In flight you lower the trailing edge flaps fully down, the …

stalling angle increases and the L/D ratio reduces

stalling angle reduces and the LM ratio increases

wing CP moves forward and the L/D ratio increases

wing CP moves aft and the L/D ratio decreases

Which ratio is defined as the "aspect ratio" of a wing?

Square of the span and the gross wing area

Square of the span and the mean chord

Square of the span and the net wing area

Ratio between wing span and gross wing area

The span-wise flow on an unswept wing is from:

The lower surface via the trailing edge to the upper wing surface

The upper surface via the trailing edge to the lower wing surface

The lower to the upper surface via the wing tip

The upper surface via the leading edge to the lower wing surface

081 POF Fragen

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