mod 8

90問 • 1ヶ月前

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問題一覧

gases proportions in the atmosphere are in the following (by volume

Nitrogen 78% Oxygen 21

Weather systems exists in the

troposphere only

The tropopause occurs where

the temperature ceases to decrease as altitude increases

Ozone is mainly found in

stratosphere and troposphere

Temperature is a measure of

the internal kinetic energy of a substance As temperature increases, the molecular movement of the substance Increases

Lapse rate is referred to

the decrease of temperature with an increase of height

Lapse rate comparable value of

1.98°c/1000ft often rounded 2°c/1000 ft

In aviation the actual atmospheric temperature is very often expressed

as the outside air temperature (OAT

At high temperature airfield a longer take-off run is

required for a fixed throttle setting

Standard sea level temperature

is 15 degrees Celsius

Isobars used on a weather map are

lines of equal pressure

pressure is caused by

the mass air acting under the force of gravity on a given area

It should be noted that at about 18,000 ft. the pressure

is half the sea level value

pressure altitude

The height that a given pressure occurs

Absolute pressure

= Gauge pressure + Atmospheric pressure

A gauge pressure of 25,3 PSI (in the International Standard Atmosphere) what is absolute pressure

40.0 PSI

Density is

expressed in grams, or kilograms per cubic meters for metric or SI units

reduction in air density

reduces the wing’s lift

Air at low altitude

has the greater density

It is possible to change the static pressure of air by forcing the

air through a venture tube. As air flows through a narrowing port, its static pressure will decrease

The airspeed indicator uses pitot pressure inside the capsule, and static pressure outside the capsule and

thus measures dynamic pressure

dew point

is the temperature to which humid air must be cooled at a constant pressure to become saturated

As an incompressible fluid flows through a duct of varying cross sectional area, the mass flow rate remains constant. this is defined as

the principle of continuity

Ground speed can be determined

by the vector sum of the aircraft's true airspeed and the current wind speed and direction.

The resultant airflow that affects the wing is made

by the relative horizontal and vertical airflow components.

The chord line of a wing is a line that

runs from the centre of the leading edge of the wing to the trailing edge.

Angle of attack

is the angle between oncoming air (or relative airflow) and the chord line of the wing.

An increase in the angle of attack will cause

the centre of pressure to move forward

when trailing edge flaps are deployed, the camber and the angle of attack are both

increased

An increase in aircraft weight

will increase the stall speed

In straight and level flight

lift = weight, and thrust = drag

Rate of climb is dependent upon

excess power

The glide ratio is the same as the

lift/drag ratio

The best gliding angle is achieved by using the angle of attack that gives

the best L/D ratio

Compared to straight and level flight, when an aeroplane is turning

stall speed increases and load factor increases

A minimum radius turn is easier achieved

at low altitude

During a turn, for any given speed

the radius of turn will depend upon the angle of bank

An increase in altitude will cause the rate of turn

to decrease

To achieve a maximum rate turn, it can be shown that

Wing loading must be as low as possible

Flaps at landing position

decrease landing speed

The load factor of a given aircraft in a given condition of flight is defined as

the lift divided by the weight

During a turn

insufficient rudder causes slip

Fowler flap

increases the area of the wing

A winglet

reduces drag and increases thrust

Winglets

reduce tip vortices, increasing the effective aspect ratio

Ground effect results

in increased lift and reduced drag

Ground effect

interferes’ with the formation of the tip vortices.

In the case of an aircraft making a turn, the force causing centripetal acceleration

is the horizontal component of the lift acting on the aircraft

A standard rate turn is defined as a 3° per second turn, which completes a 360° turn in 2 minutes

This is known as a 2-minute turn or rate one (180°/min)

The power provided by jet and piston engines alike decrease with altitude

due mainly to decreasing air density

When an aeroplane is in an unpowered descent, a component of the weight

acts forwards along the flight path, and provides the ‘thrust’ to drive the aeroplane forwards against the drag

In any manoeuvre, the stalling speed is

proportional to the square root of the load factor

When a turn is executed without any skid or slip, it

is called a coordinated turn

Movement about the normal axis is called

yawing

Primary controls

ailerons, elevator (or, in some installations, stabilator) rudder

If aircraft moves in roll the axis it is moving about

is Longitudinal

Stability of an aircraft

is the tendency of the aircraft to return to its original trimmed position after having been displaced

incorporation of an artificial stability mechanism, using sensors, computers and inputs to the aircraft’s trim or primary control systems

this is known as active stability

If, after disturbance, an aeroplane initially returns to its equilibrium state.

It has static stability and may be dynamically stable

Moving the centre of gravity forward, away from the centre of pressure will

increase longitudinal stability

If horizontal stabilizer is re-positioned to a location further from the aircraft’s centre of gravity

it will Increase the aircraft’s longitudinal stability.

Blanketing effect will increase

lateral stability

When an aeroplane with swept wings sideslips, the leading wing has

greater span than the trailing wing

Porpoising

is a longitudinal instability

Dihedral

is an outward and upward inclination of the wings to increases lateral stability.

High winged aircraft usually have less dihedral than low winged aircraft

because the pendulum effect of a high winged aircraft provides a considerable amount of lateral stability

Anhedral

is an outwards and downward inclination of the wings to reduce stability.

Blanketing effect will increase

lateral stability

If the aeroplane is loaded with the centre of gravity too far aft

the aeroplane may assume a nose up rather than a nose down attitude

Longitudinal stability is pitch stability, or stability around

the lateral axis of the aeroplane

Positive longitudinal dynamic stability is provided solely

by the horizontal stabiliser

The aero foil produces zero lift at a certain

negative angle of attack

Drag acts in a direction parallel with the relative airflow, and is therefore

always perpendicular to lift (where generated

the aspect ratio of a wing is the ratio of

its span to its aerodynamic chord

A wing of area 12 m² and span of 12m has an aspect ratio of

Wing loading is calculated by

weight divided by gross wing area

Longitudinal dihedral angle is defined asLongitudinal dihedral angle is defined as

the difference the angle of incidence of the mainplane and tailplane

Wing tip vortices on conventional aeroplanes create

additional drag and reduce lift

Skin friction drag increases with

increasing turbulent boundary layer

Friction drag can be reduced by

delaying the point at which laminar flow becomes turbulent

Induced drag

is greater at low aspect ratio wing

Profile drag

increases with the square of the IAS

If the weight of an aircraft is increased

minimum drag speed will increase

Vortex generators

move the transition point forwards towards the leading edge of the wing

Dogtooth extensions, leading edge cuffs and vortillons are all designed to

prevent wing tip stalling at low speed

At small angle of attack the Cp is located between

40to 50% of the chord

If an aircraft with swept wings begins to tip-stall

it will pitch up

Accretion of ice on

a wing will increase stall speed

The normal axis of an aircraft passes

through the center of gravity

Directional stability is stability about

the normal axis

問題一覧

gases proportions in the atmosphere are in the following (by volume

Nitrogen 78% Oxygen 21

Weather systems exists in the

troposphere only

The tropopause occurs where

the temperature ceases to decrease as altitude increases

Ozone is mainly found in

stratosphere and troposphere

Temperature is a measure of

the internal kinetic energy of a substance As temperature increases, the molecular movement of the substance Increases

Lapse rate is referred to

the decrease of temperature with an increase of height

Lapse rate comparable value of

1.98°c/1000ft often rounded 2°c/1000 ft

In aviation the actual atmospheric temperature is very often expressed

as the outside air temperature (OAT

At high temperature airfield a longer take-off run is

required for a fixed throttle setting

Standard sea level temperature

is 15 degrees Celsius

Isobars used on a weather map are

lines of equal pressure

pressure is caused by

the mass air acting under the force of gravity on a given area

It should be noted that at about 18,000 ft. the pressure

is half the sea level value

pressure altitude

The height that a given pressure occurs

Absolute pressure

= Gauge pressure + Atmospheric pressure

A gauge pressure of 25,3 PSI (in the International Standard Atmosphere) what is absolute pressure

40.0 PSI

Density is

expressed in grams, or kilograms per cubic meters for metric or SI units

reduction in air density

reduces the wing’s lift

Air at low altitude

has the greater density

It is possible to change the static pressure of air by forcing the

air through a venture tube. As air flows through a narrowing port, its static pressure will decrease

The airspeed indicator uses pitot pressure inside the capsule, and static pressure outside the capsule and

thus measures dynamic pressure

dew point

is the temperature to which humid air must be cooled at a constant pressure to become saturated

As an incompressible fluid flows through a duct of varying cross sectional area, the mass flow rate remains constant. this is defined as

the principle of continuity

Ground speed can be determined

by the vector sum of the aircraft's true airspeed and the current wind speed and direction.

The resultant airflow that affects the wing is made

by the relative horizontal and vertical airflow components.

The chord line of a wing is a line that

runs from the centre of the leading edge of the wing to the trailing edge.

Angle of attack

is the angle between oncoming air (or relative airflow) and the chord line of the wing.

An increase in the angle of attack will cause

the centre of pressure to move forward

when trailing edge flaps are deployed, the camber and the angle of attack are both

increased

An increase in aircraft weight

will increase the stall speed

In straight and level flight

lift = weight, and thrust = drag

Rate of climb is dependent upon

excess power

The glide ratio is the same as the

lift/drag ratio

The best gliding angle is achieved by using the angle of attack that gives

the best L/D ratio

Compared to straight and level flight, when an aeroplane is turning

stall speed increases and load factor increases

A minimum radius turn is easier achieved

at low altitude

During a turn, for any given speed

the radius of turn will depend upon the angle of bank

An increase in altitude will cause the rate of turn

to decrease

To achieve a maximum rate turn, it can be shown that

Wing loading must be as low as possible

Flaps at landing position

decrease landing speed

The load factor of a given aircraft in a given condition of flight is defined as

the lift divided by the weight

During a turn

insufficient rudder causes slip

Fowler flap

increases the area of the wing

A winglet

reduces drag and increases thrust

Winglets

reduce tip vortices, increasing the effective aspect ratio

Ground effect results

in increased lift and reduced drag

Ground effect

interferes’ with the formation of the tip vortices.

In the case of an aircraft making a turn, the force causing centripetal acceleration

is the horizontal component of the lift acting on the aircraft

A standard rate turn is defined as a 3° per second turn, which completes a 360° turn in 2 minutes

This is known as a 2-minute turn or rate one (180°/min)

The power provided by jet and piston engines alike decrease with altitude

due mainly to decreasing air density

When an aeroplane is in an unpowered descent, a component of the weight

acts forwards along the flight path, and provides the ‘thrust’ to drive the aeroplane forwards against the drag

In any manoeuvre, the stalling speed is

proportional to the square root of the load factor

When a turn is executed without any skid or slip, it

is called a coordinated turn

Movement about the normal axis is called

yawing

Primary controls

ailerons, elevator (or, in some installations, stabilator) rudder

If aircraft moves in roll the axis it is moving about

is Longitudinal

Stability of an aircraft

is the tendency of the aircraft to return to its original trimmed position after having been displaced

incorporation of an artificial stability mechanism, using sensors, computers and inputs to the aircraft’s trim or primary control systems

this is known as active stability

If, after disturbance, an aeroplane initially returns to its equilibrium state.

It has static stability and may be dynamically stable

Moving the centre of gravity forward, away from the centre of pressure will

increase longitudinal stability

If horizontal stabilizer is re-positioned to a location further from the aircraft’s centre of gravity

it will Increase the aircraft’s longitudinal stability.

Blanketing effect will increase

lateral stability

When an aeroplane with swept wings sideslips, the leading wing has

greater span than the trailing wing

Porpoising

is a longitudinal instability

Dihedral

is an outward and upward inclination of the wings to increases lateral stability.

High winged aircraft usually have less dihedral than low winged aircraft

because the pendulum effect of a high winged aircraft provides a considerable amount of lateral stability

Anhedral

is an outwards and downward inclination of the wings to reduce stability.

Blanketing effect will increase

lateral stability

If the aeroplane is loaded with the centre of gravity too far aft

the aeroplane may assume a nose up rather than a nose down attitude

Longitudinal stability is pitch stability, or stability around

the lateral axis of the aeroplane

Positive longitudinal dynamic stability is provided solely

by the horizontal stabiliser

The aero foil produces zero lift at a certain

negative angle of attack

Drag acts in a direction parallel with the relative airflow, and is therefore

always perpendicular to lift (where generated

the aspect ratio of a wing is the ratio of

its span to its aerodynamic chord

A wing of area 12 m² and span of 12m has an aspect ratio of

Wing loading is calculated by

weight divided by gross wing area

Longitudinal dihedral angle is defined asLongitudinal dihedral angle is defined as

the difference the angle of incidence of the mainplane and tailplane

Wing tip vortices on conventional aeroplanes create

additional drag and reduce lift

Skin friction drag increases with

increasing turbulent boundary layer

Friction drag can be reduced by

delaying the point at which laminar flow becomes turbulent

Induced drag

is greater at low aspect ratio wing

Profile drag

increases with the square of the IAS

If the weight of an aircraft is increased

minimum drag speed will increase

Vortex generators

move the transition point forwards towards the leading edge of the wing

Dogtooth extensions, leading edge cuffs and vortillons are all designed to

prevent wing tip stalling at low speed

At small angle of attack the Cp is located between

40to 50% of the chord

If an aircraft with swept wings begins to tip-stall

it will pitch up

Accretion of ice on

a wing will increase stall speed

The normal axis of an aircraft passes

through the center of gravity

Directional stability is stability about

the normal axis