Set of flashcards Principles of Flight

Flashcards	149
Language	English
Category	Technology
Level	University
Created / Updated	25.12.2024 / 20.01.2025
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Why are the flaps usually not fully extended at take-off?

Because the aeroplane would have a too heavy nose-down moment

Because the drag would be too high

Because the lift would be too high

Because the flaps could be overstressed

A take-off with flaps in take-off position causes...

an increased rate of climb.

a decrease in drag.

an increased acceleration.

a shortening of the take-off run.

Provided that no other procedure is described in the Aircraft Operating Handbook, after increasing the engine power in a go-around, the flaps may...

be retracted to a middle position.

not be operated up to the minimum safe altitude.

be fully retracted without any delay.

remain fully extended until reaching the traffic pattern.

How do lift and drag change when setting flaps to a lower position?

Lift increases, drag increases

Lift increases, drag decreases

Lift decreases, drag increases

Lift decreases, drag decreases

What has to be considered when flaps are retracted?

Retraction of flaps is always possible without any loss of lift

Close to the ground, flaps may only be retracted stepwise at a safe height

When approaching too low, flaps should be retracted to provide a better gliding angle

When going around, flaps should be fully retracted immediately

The boundary layer turns from laminar to turbulent at the...

separation point.

transition point.

center of pressure.

stagnation point.

The laminar layer on the aerofoil is located between...

the transition point and the separation point.

the stagnation point and the transition point.

the stagnation point and the center of pressure.

the transition point and the center of pressure.

What types of boundary layers can be found on an aerofoil?

Laminar boundary layer along the complete upper surface with non-separated airflow

Turbulent boundary layer along the complete upper surface with separated airflow

Turbulent layer at the leading wing areas, laminar boundary layer at the trailing areas

Laminar layer at the leading wing areas, turbulent boundary layer at the trailing areas

How does a laminar boundary layer differ from a turbulent boundary layer?

The turbulent boundary layer can follow the airfoil camber at higher angles of attack

The laminar boundary layer is thinner and provides more skin-friction drag

The turbulent boundary layer is thicker and provides less skin-friction drag

The laminar boundary layer produces lift, the turbulent boundary layer produces drag

In icing conditions, at which point will the most ice arise on an aeroplane?

On the upper and lower side of the control surfaces

On the pitot tube and the static pressure ports

On the upper and lower side of the wing's trailing edge

On all frontal areas of the airframe, the wings, and the tail

"Lateral stability" is referred to as stability around which axis?

Lateral axis

Vertical axis

Longitudinal axis

Rotational axis

What structural item provides lateral stability to an airplane?

Vertical tail

Elevator

Differential aileron deflection

Wing dihedral

Which statement describes a situation of static stability?

An aircraft distorted by external impact will maintain the deflected position

An aircraft distorted by external impact will return to the original position

An aircraft distorted by external impact will tend to an even more deflected position

An aircraft distorted by external impact can return to its original position by rudder input

A statically unstable aeroplane...

is always dynamically stable.

becomes more stable with a rear centre of gravity.

can never be dynamically stable.

becomes more stable at higher speeds.

Which force does NOT act during straight and level flight?

Lift force

Centrifugal force

Gravitational force

Drag force

Which constructive feature is shown in the figure? See figure (PFA-006) L: Lift

Directional stability by lift generation

Lateral stability by wing dihedral

Differential aileron deflection

Longitudinal stability by wing dihedral

Which constructive feature provides longitudinal stability to an airplane in normal configuration (empennage at tail)?

Differential aileron deflection

Downforce at the elevator

Positive wing dihedral

Trim plate at the tailfin

"Longitudinal stability" is referred to as stability around which axis?

Vertical axis

Longitudinal axis

Lateral axis

Propeller axis

Stability around which axis is strongly influenced by the center of gravity's position?

Longitudinal axis

Vertical axis

Gravity axis

Lateral axis

"Directional stability" is referred to as stability around which axis?

Vertical axis

Directional axis

Lateral axis

Longitudinal axis

What structural item provides directional stability to an airplane?

Wing dihedral

Large vertical tail

Large elevator

Differential aileron deflection

An aircraft can move around which axes?

Vertical axis, front axis, longitudinal axis

Central axis, vertical axis, longitudinal axis

Lateral axis, longitudinal axis, vertical axis

Longitudinal axis, vertical axis, front axis

Rotation around the vertical axis is called...

yawing

slipping

rolling

pitching

Rotation around the lateral axis is called...

yawing

pitching

rolling

stalling

Rotation around the longitudinal axis is called...

pitching

yawing

rolling

rotating

The critical angle of attack...

decreases with a rear centre of gravity.

is not changed by different aircraft weights.

increases with a front centre of gravity.

is changed by different aircraft weights.

In straight and level flight with constant performance of the engine, the angle of attack at the wing is...

greater than in a climb.

smaller than in a climb.

greater than at take-off.

smaller than in a descent.

What is the function of the elevator (among other things)?

To stabilise the aeroplane around the longitudinal axis

To stabilise the aeroplane around the vertical axis

To stabilise the aeroplane around the lateral axis

To initiate a curve around the vertical axis

The elevator deflection for a specific maneuver...

is increased with a front centre of gravity.

is increased at high speeds.

is increased with a rear centre of gravity.

is independent of the speed.

Rotation around the lateral axis is called...

pitch

roll

yaw

slip

The elevator moves an aeroplane around the...

vertical axis

lateral axis

longitudinal axis

elevator axis

Deflecting the elevator upwards results in...

lowering the aircraft's nose

shifting the center of gravity ahead

shifting the center of gravity backwards

raising the aircraft's nose

What has to be considered with regard to the center of gravity position?

Only correct loading can assure a correct and safe center of gravity position

By moving the elevator trim tab, the center of gravity can be shifted into a correct position

By moving the aileron trim tab, the center of gravity can be shifted into a correct position

The center of gravity's position can only be determined during flight

A rotation around the vertical axis is called...

pitch

slip

roll

yaw

Rudder deflections result in a turn of the aeroplane around the...

vertical axis

lateral axis

longitudinal axis

rudder axis

Deflecting the rudder to the left causes...

yawing of the aircraft to the right

yawing of the aircraft to the left

pitching of the aircraft to the left

pitching of the aircraft to the right

Which deflection of the ailerons can be observed during a turn to the left?

Both ailerons upwards

Both ailerons downwards

Left aileron upwards, right aileron downwards

Left aileron downwards, right aileron upwards

Which deflection of differential ailerons can be observed during a turn to the right?

The right aileron moves down more than the left aileron moves up

The right aileron moves up more than the left aileron moves down

The right aileron moves up more than the left aileron

The right aileron moves down more than the left aileron

What is the advantage of differential aileron movement?

The adverse yaw is higher

The ratio of the drag coefficient to lift coefficient is increased

The drag of the downwards deflected aileron is lowered and the adverse yaw is smaller

The total lift remains constant during aileron deflection

Which design feature can compensate for adverse yaw?

Aileron trim

Differential aileron deflection

Wing dihedral

Full deflection of the aileron

Principles of Flight - AC

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