Aeroscience

Questão 1 de 40

1

A fly-by-wire system is one that:

Selecione uma das seguintes:

Requires the pilot to stabilise the aircraft manually
Uses a system of wires connected to pulleys linked to the pilot’s controls
Converts the movements of flight controls to electronic signals that are transmitted by wires, and uses flight control computers to determine how to move the actuators at each control surface to provide the ordered response
Uses a system consisting of three gyroscopes and three accelerometers

Explicação

Questão 2 de 40

1

A Shock stall is:

Selecione uma das seguintes:

1. Also known as a high-speed stall
2. The breakdown in lift as the result of a shock wave
3. When an aerofoil exceeds the critical angle and there is insufficient lift to support the aircraft's weight, causing the aircraft to stall
4. Both 1 and 2 are correct

Explicação

Questão 3 de 40

1

An aircraft takes off with an IAS of 200 kt and maintains the IAS to an altitude of 31,000 ft. What would the Mach number at 10,000 ft be compared to at 31,000 ft?

Selecione uma das seguintes:

Lower
Higher

Explicação

Questão 4 de 40

1

As subsonic flow converges, the velocity and the pressure , while the density is said to __.

Selecione uma das seguintes:

decreases, increases, remain constant
decreases, increases, decrease
increases, decreases, remain constant
increases, decreases, decrease

Explicação

Questão 5 de 40

1

As subsonic flow diverges, the velocity and the pressure , while the density is said to __.

Selecione uma das seguintes:

decreases, increases, increase
increases, decreases, remain constant
increases, decreases, increase
decreases, increases, remain constant

Explicação

Questão 6 de 40

1

As supersonic flow converges, the velocity and the pressure , while the density and temperature is said to __.

Selecione uma das seguintes:

decreases, increases, increase
increases, decreases, decrease
increases, decreases, increase
decreases, increases, decrease

Explicação

Questão 7 de 40

1

As supersonic flow diverges, the velocity and the pressure , while the density and temperature is said to __.

Selecione uma das seguintes:

decreases, increases, decrease
decreases, increases, increase
increases, decreases, increase
increases, decreases, decrease

Explicação

Questão 8 de 40

1

At what speed does the detached bow wave form?

Selecione uma das seguintes:

Beyond MFS 2.0
MCRIT to 1.0
MFS 1.1–1.5
MCRIT

Explicação

Questão 9 de 40

1

Coffins corner is:

Selecione uma das seguintes:

When the TAS and MCRIT/MMO arrive at the same value
When the stall speed and MCRIT/MMO arrive at the same value
When the stall speed and TAS arrive at the same value
When the TAS and LSS arrive at the same value

Explicação

Questão 10 de 40

1

Critical Mach number (MCRIT) is defined as:

Selecione uma das seguintes:

The Mach number relative to the local speed of sound measured at a specific point on the aircraft. Depending on where this measurement is taken, this speed may be greater or less than the free-stream Mach number.
The Mach number of the airflow at a point unaffected by the pressure of the aircraft but measured relative to it
The Mach number of the airflow at a point where the drag coefficient rapidly rises. This is due to the flow separation and adverse pressure gradient behind the shock wave.
The lowest free-stream Mach number at which a local Mach number of 1.0 will occur at any point on the aircraft

Explicação

Questão 11 de 40

1

For an aircraft to be laterally stable:

Selecione uma das seguintes:

It must have the ability to return to normal following a stall.
It must have the ability to return to normal following a disturbance about the vertical axis.
It must have the ability to return to normal following a disturbance about the longitudinal axis.
It must have the ability to return to normal following a disturbance about the lateral axis.

Explicação

Questão 12 de 40

1

How is the wingtip vortex reduced?

Selecione uma das seguintes:

Winglets
Wing fences
Leading-edge sawtooth
All of these

Explicação

Questão 13 de 40

1

If an aircraft were climbing at constant Mach above the tropopause, IAS would , and TAS would .

Selecione uma das seguintes:

increase; decrease
decrease; remain constant
remain constant; decrease
decrease; decrease

Explicação

Questão 14 de 40

1

Mach buffet is:

Selecione uma das seguintes:

The decreased turbulent flow behind the shock wave. It strikes the tailplane section with enough force to buffet the controls.
An aerofoil exceeding the critical angle. The airflow breaks away from the aerofoil and strikes the tailplane.
A low-speed buffet
The increased turbulent flow behind the shock wave. It strikes the tailplane section with enough force to buffet the controls.

Explicação

Questão 15 de 40

1

Mach Number is defined as:

Selecione uma das seguintes:

The ratio of the indicated airspeed (IAS) to the local speed of sound (LSS)
The ratio of the calibrated airspeed (CAS) to the local speed of sound (LSS)
The ratio of the local speed of sound (LSS) to the true airspeed (TAS)
The ratio of the true airspeed (TAS) to the local speed of sound (LSS)

Explicação

Questão 16 de 40

1

Select the most correct answer in regards to Mack tuck.

Selecione uma das seguintes:

As an aircraft accelerates through the transonic range, the centre of pressure moves rearwards in conjunction with the aft-moving spread of supersonic flow. From a starting position of approximately 15% of the chord, the C of P may end up at 20% chord, well behind the point of maximum camber (depending on the wing). This rearward shift of the C of P increases the moment arm between the centre of pressure and the centre of gravity, causing a nose-down pitching moment.
As an aircraft accelerates through the transonic range, the centre of pressure moves forwards in conjunction with the aft-moving spread of supersonic flow. From a starting position of approximately 25% of the chord, the C of P may end up at 50% chord, well behind the point of maximum camber (depending on the wing). This forward shift of the C of P increases the moment arm between the centre of pressure and the centre of gravity, causing a nose-down pitching moment.
As an aircraft accelerates through the transonic range, the centre of pressure moves rearwards in conjunction with the aft-moving spread of supersonic flow. From a starting position of approximately 25% of the chord, the C of P may end up at 50% chord, well behind the point of maximum camber (depending on the wing). This rearward shift of the C of P increases the moment arm between the centre of pressure and the centre of gravity, causing a nose-down pitching moment.
As an aircraft accelerates through the transonic range, the centre of pressure moves rearwards in conjunction with the aft-moving spread of supersonic flow. From a starting position of approximately 5% of the chord, the C of P may end up at 70% chord, well behind the point of maximum camber (depending on the wing). This rearward shift of the C of P increases the moment arm between the centre of pressure and the centre of gravity, causing a nose-down pitching moment.

Explicação

Questão 17 de 40

1

State the speed of sound formula.

Selecione uma das seguintes:

38.94 × √T°K
39.84 × √T°K
38.94 × √T°C
39.84 × √T°C

Explicação

Questão 18 de 40

1

The area rule states that:

Selecione uma das seguintes:

The aircraft should be as large as possible.
The aircraft should be as small as possible.
The aerodynamic shape of the surface in question should change in cross-sectional area as sharply as possible, increasing rapidly to a maximum, then decreasing just as rapidly.
The aerodynamic shape of the surface in question should change in cross-sectional area as smoothly as possible, increasing gradually to a maximum, then decreasing just as gradually.

Explicação

Questão 19 de 40

1

The main benefit of a sweptback wing is:

Selecione uma das seguintes:

A higher critical angle
A lower critical angle
The decreased critical Mach number
The increased critical Mach number

Explicação

Questão 20 de 40

1

The only thing that affects the speed of sound through the air is:

Selecione uma das seguintes:

Air density
Air temperature
Air pressure
Air pollution

Explicação

Questão 21 de 40

1

The speed of sound is defined as:

Selecione uma das seguintes:

The distance travelled by a sound wave propagating through the air
The distance travelled by a light wave propagating through a given medium
The distance travelled by a sound wave propagating through a given medium
The distance travelled by a sound wave propagating through the water

Explicação

Questão 22 de 40

1

The transonic range is typically between:

Selecione uma das seguintes:

Mach 0.8 and below (approx. 530 kt)
Mach 0.8 and 1.2 (approx. 530–790 kt)
Mach 1.2 and 5.0 (approx. 790–300 kt)
Mach 5.0 and 10.0 (approx. 3,300–6,600 kt)

Explicação

Questão 23 de 40

1

What does number 2 on the graph correspond to?

Selecione uma das seguintes:

Critical drag rise Mach number (also known as drag divergence Mach number, or MCDR) is reached. This is the Mach number where the amount of drag experienced rapidly rises. The large increase in drag is caused by the formation of a shock wave on the upper surface of the airfoil.
The MFS reaches Mach 1.0.
MDET is reached. This is the speed where all airflow over the aircraft is supersonic. The amount of drag is slightly higher than the subsonic range due to the presence of the bow wave.
MCRIT is reached.

Explicação

Questão 24 de 40

1

Wave drag is:

Selecione uma das seguintes:

A form of induced drag
The drag caused by the turbulent boundary layer generated by the shock wave.
Typically seen on aircraft flying in the subsonic speed range
Typically seen on aircraft flying in the supersonic speed range

Explicação

Questão 25 de 40

1

What does the number 3 correspond to on the graph?

Selecione uma das seguintes:

MDET is reached, where all airflow over the wing is supersonic (>M1.0). The detached bow wave has formed and interferes with the airflow over the wing. Although a stable flow, lift is slightly reduced.
Both shock waves, above and below the wing, have reached the trailing edge. The airflow over the wing is now supersonic, and a stable laminar flow is aiding in the production of lift.
CL increases with an increase in speed. The airflow accelerates over the wing, increasing lift. MCRIT is reached where the airflow over the aircraft is now supersonic in some places
Shock waves formed above and below the wing interfere with the airflow behind the shock wave. This causes separation of the air from the wing behind the shock wave, creating drag and the reduction in lift.

Explicação

Questão 26 de 40

1

What effect does increasing the angle of attack have on critical Mach number?

Selecione uma das seguintes:

Reduces the critical Mach number. When you increase angle of attack, you are effectively increasing the velocity of the air over the upper section of the aerofoil. As a result, the first shock wave (normal shock wave) develops at a lower free-stream Mach number, and it is for this reason that the MCRIT is reached at a lower Mach number.
Increases the critical Mach number. When you decrease angle of attack, you are effectively increasing the velocity of the air over the upper section of the aerofoil. As a result, the first shock wave (normal shock wave) develops at a lower free-stream Mach number, and it is for this reason that the MCRIT is reached at a higher Mach number.
Reduces critical Mach number. When you increase angle of attack, you are effectively decreasing the velocity of the air over the upper section of the aerofoil. As a result, the first shock wave (normal shock wave) develops at a lower free-stream Mach number, and it is for this reason that the MCRIT is reached at a lower Mach number.
Increases the critical Mach number. When you increase angle of attack, you are effectively increasing the velocity of the air over the upper section of the aerofoil. As a result, the first shock wave (normal shock wave) develops at a lower free-stream Mach number, and it is for this reason that the MCRIT is reached at a higher Mach number.

Explicação

Questão 27 de 40

1

What is the ‘crossover altitude’?

Selecione uma das seguintes:

The point where the aircraft will change from climbing at constant Mach to constant IAS
Where a descending aircraft would change from constant IAS to constant Mach
The point at which a pilot would change the subscale on the altimeters from area QNH to standard 1013 hPa
Where a climbing aircraft would change from climbing at constant IAS to constant Mach

Explicação

Questão 28 de 40

1

What would happen to the Mach and TAS of an aircraft descending at constant IAS below the tropopause?

Selecione uma das seguintes:

Mach would decrease; TAS would decrease
Mach would increase; TAS would increase
Mach would increase; TAS would decrease
Mach would decrease; TAS would increase

Explicação

Questão 29 de 40

1

Free-stream Mach number (MFS) is defined as:

Selecione uma das seguintes:

The Mach number relative to the local speed of sound measured at a specific point on the aircraft. Depending on where this measurement is taken, this speed may be greater or less than the free-stream Mach number.
The Mach number of the airflow at a point unaffected by the pressure of the aircraft but measured relative to it
The Mach number of the airflow at a point where the drag coefficient rapidly rises. This is due to the flow separation and adverse pressure gradient behind the shock wave.
The lowest free-stream Mach number at which a local Mach number of 1.0 will occur at any point on the aircraft

Explicação

Questão 30 de 40

1

Local Mach number (ML) is defined as:

Selecione uma das seguintes:

The lowest free-stream Mach number at which a local Mach number of 1.0 will occur at any point on the aircraft
The Mach number of the airflow at a point where the drag coefficient rapidly rises. This is due to the flow separation and adverse pressure gradient behind the shock wave.
The Mach number of the airflow at a point unaffected by the pressure of the aircraft but measured relative to it
The Mach number relative to the local speed of sound measured at a specific point on the aircraft. Depending on where this measurement is taken, this speed may be greater or less than the free-stream Mach number.

Explicação

Questão 31 de 40

1

Critical drag rise Mach number (MCDR) (also known as Drag Divergence Mach Number) is defined as:

Selecione uma das seguintes:

The Mach number relative to the local speed of sound measured at a specific point on the aircraft. Depending on where this measurement is taken, this speed may be greater or less than the free-stream Mach number.
The Mach number of the airflow at a point unaffected by the pressure of the aircraft but measured relative to it
The Mach number of the airflow at a point where the drag coefficient rapidly rises. This is due to the flow separation and adverse pressure gradient behind the shock wave.
The lowest free-stream Mach number at which a local Mach number of 1.0 will occur at any point on the aircraft

Explicação

Questão 32 de 40

1

Detachment Mach number (MDET) is defined as:

Selecione uma das seguintes:

The Mach number where all of the airflow over the wing is supersonic. This usually occurs around MFS 1.2 to 1.3. 
The lowest free-stream Mach number at which a local Mach number of 1.0 will occur at any point on the aircraft
The Mach number of the airflow at a point where the drag coefficient rapidly rises. This is due to the flow separation and adverse pressure gradient behind the shock wave.
The Mach number relative to the local speed of sound measured at a specific point on the aircraft. Depending on where this measurement is taken, this speed may be greater or less than the free-stream Mach number.

Explicação

Questão 33 de 40

1

The Supersonic range is typically between:

Selecione uma das seguintes:

Mach 0.8 and below (approx. 530 kt)
Mach 0.8 and 1.2 (approx. 530–790 kt)
Mach 1.0 to Mach 5.0 (approx. 790–3,300 kt)
Mach 5.0 and 10.0 (approx. 3,300–6,600 kt)

Explicação

Questão 34 de 40

1

What does the number 4 correspond to on the graph?

Selecione uma das seguintes:

MDET is reached, where all airflow over the wing is supersonic (>M1.0). The detached bow wave has formed and interferes with the airflow over the wing. Although a stable flow, lift is slightly reduced.
Both shock waves, above and below the wing, have reached the trailing edge. The airflow over the wing is now supersonic, and a stable laminar flow is aiding in the production of lift.
CL increases with an increase in speed. The airflow accelerates over the wing, increasing lift. MCRIT is reached where the airflow over the aircraft is now supersonic in some places
Shock waves formed above and below the wing interfere with the airflow behind the shock wave. This causes separation of the air from the wing behind the shock wave, creating drag and the reduction in lift.

Explicação

Questão 35 de 40

1

What does the number 5 correspond to on the graph?

Selecione uma das seguintes:

MDET is reached, where all airflow over the wing is supersonic (>M1.0). The detached bow wave has formed and interferes with the airflow over the wing. Although a stable flow, lift is slightly reduced.
Both shock waves, above and below the wing, have reached the trailing edge. The airflow over the wing is now supersonic, and a stable laminar flow is aiding in the production of lift.
CL increases with an increase in speed. The airflow accelerates over the wing, increasing lift. MCRIT is reached where the airflow over the aircraft is now supersonic in some places
Shock waves formed above and below the wing interfere with the airflow behind the shock wave. This causes separation of the air from the wing behind the shock wave, creating drag and the reduction in lift.

Explicação

Questão 36 de 40

1

What does the number 1 correspond to on the graph?

Selecione uma das seguintes:

CL increases with an increase in speed. The airflow accelerates over the wing, increasing lift. MCRIT is reached where the airflow over the aircraft is now supersonic in some places
Shock waves formed above and below the wing interfere with the airflow behind the shock wave. This causes separation of the air from the wing behind the shock wave, creating drag and the reduction in lift.
Both shock waves, above and below the wing, have reached the trailing edge. The airflow over the wing is now supersonic, and a stable laminar flow is aiding in the production of lift.
MDET is reached, where all airflow over the wing is supersonic (>M1.0). The detached bow wave has formed and interferes with the airflow over the wing. Although a stable flow, lift is slightly reduced.

Explicação

Questão 37 de 40

1

What does number 3 on the graph correspond to?

Selecione uma das seguintes:

The MFS reaches Mach 1.0.
MDET is reached. This is the speed where all airflow over the aircraft is supersonic. The amount of drag is slightly higher than the subsonic range due to the presence of the bow wave.
Critical drag rise Mach number (also known as drag divergence Mach number, or MCDR) is reached. This is the Mach number where the amount of drag experienced rapidly rises. The large increase in drag is caused by the formation of a shock wave on the upper surface of the airfoil.
MCRIT is reached.

Explicação

Questão 38 de 40

1

What does number 4 on the graph correspond to?

Selecione uma das seguintes:

MCRIT is reached
Critical drag rise Mach number (also known as drag divergence Mach number, or MCDR) is reached. This is the Mach number where the amount of drag experienced rapidly rises. The large increase in drag is caused by the formation of a shock wave on the upper surface of the airfoil.
The MFS reaches Mach 1.0.
MDET is reached. This is the speed where all airflow over the aircraft is supersonic. The amount of drag is slightly higher than the subsonic range due to the presence of the bow wave.

Explicação

Questão 39 de 40

1

If an aircraft were climbing at constant IAS above the tropopause, the Mach number would , and TAS would .

Selecione uma das seguintes:

Increase, Increase
Increase, Decrease
Decrease, Decrease
Decrease, Increase

Explicação

Questão 40 de 40

1

Dutch roll is characterised by __________________________________________. This is a form of oscillatory instability that is characterised by a combined rolling and yawing motion in which the rolling motion dominates.

Selecione uma das seguintes:

stronger lateral stability with weaker directional stability
stronger lateral stability and strong directional stability
weaker lateral stability with stronger directional stability
weak lateral stability with weaker directional stability

	Criado por Andrew Lee aproximadamente 10 anos atrás

NZCAA ATPL Aeroscience

Aeroscience

Questão 1 de 40

A fly-by-wire system is one that:

Selecione uma das seguintes:

Explicação

Questão 2 de 40

A Shock stall is:

Selecione uma das seguintes:

Explicação

Questão 3 de 40

An aircraft takes off with an IAS of 200 kt and maintains the IAS to an altitude of 31,000 ft. What would the Mach number at 10,000 ft be compared to at 31,000 ft?

Selecione uma das seguintes:

Explicação

Questão 4 de 40

As subsonic flow converges, the velocity __________ and the pressure __________, while the density is said to __________.

Selecione uma das seguintes:

Explicação

Questão 5 de 40

As subsonic flow diverges, the velocity __________ and the pressure __________, while the density is said to __________.

Selecione uma das seguintes:

Explicação

Questão 6 de 40

As supersonic flow converges, the velocity __________ and the pressure __________, while the density and temperature is said to __________.

Selecione uma das seguintes:

Explicação

Questão 7 de 40

As supersonic flow diverges, the velocity __________ and the pressure __________, while the density and temperature is said to __________.

Selecione uma das seguintes:

Explicação

Questão 8 de 40

At what speed does the detached bow wave form?

Selecione uma das seguintes:

Explicação

Questão 9 de 40

Coffins corner is:

Selecione uma das seguintes:

Explicação

Questão 10 de 40

Critical Mach number (MCRIT) is defined as:

Selecione uma das seguintes:

Explicação

Questão 11 de 40

For an aircraft to be laterally stable:

Selecione uma das seguintes:

Explicação

Questão 12 de 40

How is the wingtip vortex reduced?

Selecione uma das seguintes:

Explicação

Questão 13 de 40

If an aircraft were climbing at constant Mach above the tropopause, IAS would __________, and TAS would __________.

Selecione uma das seguintes:

Explicação

Questão 14 de 40

Mach buffet is:

Selecione uma das seguintes:

Explicação

Questão 15 de 40

Mach Number is defined as:

Selecione uma das seguintes:

Explicação

Questão 16 de 40

Select the most correct answer in regards to Mack tuck.

Selecione uma das seguintes:

Explicação

Questão 17 de 40

State the speed of sound formula.

Selecione uma das seguintes:

Explicação

Questão 18 de 40

The area rule states that:

Selecione uma das seguintes:

Explicação

Questão 19 de 40

The main benefit of a sweptback wing is:

Selecione uma das seguintes:

Explicação

Questão 20 de 40

The only thing that affects the speed of sound through the air is:

As subsonic flow converges, the velocity and the pressure , while the density is said to __.

As subsonic flow diverges, the velocity and the pressure , while the density is said to __.

As supersonic flow converges, the velocity and the pressure , while the density and temperature is said to __.

As supersonic flow diverges, the velocity and the pressure , while the density and temperature is said to __.

If an aircraft were climbing at constant Mach above the tropopause, IAS would , and TAS would .