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AERT 4040 Flashcards

Aerodynamics

1
Q

Density Altitude is used as a predictor of aircraft performance, not as a height reference.
True
False

A

True

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2
Q

An aircraft’s Mach Number is the aircraft’s

Local Speed of Sound divided by TAS

IAS divided by the Local Speed of Sound

TAS divided by the Local Speed of Sound

A

TAS divided by the Local Speed of Sound

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3
Q

The temperature and pressure conditions for a standard day are ______________.

59 degrees F / 15 degrees C and 29.92 in of Hg / 1013 mbar

There is no such thing as a standard day

68 degrees F / 20 degrees C and 30.30 in of Hg / 1026 mbar

A

59 degrees F / 15 degrees C and 29.92 in of Hg / 1013 mbar

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4
Q

What did the Wright brothers think was the most difficult problem, thus the first problem they attacked when building their Flyer?

Design of the wings

How to control and balance the aircraft

Developing a means of propulsion

A

How to control and balance the aircraft

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5
Q

Density is

is always expressed by Liters per Pound

Mass per unit volume

Weight per unit volume

A

Mass per unit volume

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6
Q

The Critical Mach Number of an aircraft is the highest Mach Number the aircraft can travel before structural damage is done to the airframe.
True
False

A

False

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7
Q

How did the Wrights correct their problem of roll reversal?

They used a canard rather than an elevator

They used counter-rotations propellers

They developed a movable rudder and connected it to the roll control

A

They developed a movable rudder and connected it to the roll control

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8
Q

What method did the Wright brothers use to control roll?

The used what was later called flight spoilers

They developed a technique of wing warping

They developed ailerons

A

They developed a technique of wing warping

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9
Q

The speed of sound in air is dependent upon the

Air Density only

A combination of Air Temperature, Air Density and Humidity

Air Temperature only

A

Air Temperature only

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10
Q

What was unique about the engine that the Wrights used for their Flyer?

It was the first time aluminum was used in the construction od an aircraft

It was the first use of 100 LL fuel

It was the first use of a six cylinder engine

A

It was the first time aluminum was used in the construction od an aircraft

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11
Q

Air viscosity __________ as the air temperature increases.

Increases

Stays the same

Decreases

A

increases

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12
Q

Total pressure is:

measured parallel to the local stream

1/2ρV²

static pressure minus dynamic pressure

static pressure plus dynamic pressure

A

static pressure plus dynamic pressure

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13
Q

The General Gas Law sets the relationship between three properties of air: pressure (P), density (ρ), and temperature (T). It is expressed as an equation where R is a constant for any given gas. What is the correct expression of the General Gas Law.

ρT = PR

ρP = RT

ρ = P/RT

ρPT =

A

ρ = P/RT

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14
Q

The Law of Interaction states __________.

“Two opposite forces cannot interact.”

“An unbalanced force acting upon a body produces an acceleration in the direction of the force that is directly proportional to the force and inversely proportional to the mass of the body.”

“A body at rest tends to stay at rest.”

“For every action there is an equal and opposite reaction.”

A

“For every action there is an equal and opposite reaction.”

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15
Q

The angle of incidence of a wing is the angle between a line drawn through the 25% cord points and a line drawn parallel to the lateral axis.
True
Fasle

A

False

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16
Q

Static pressure acts:

in the direction of the flow

perpendicular to the surface that any air molecules collide with.

perpendicular to the direction of flow

in the direction of the total pressure

A

perpendicular to the surface that any air molecules collide with.

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17
Q

A moment is _________.

created when a force is applied at some distance from an axis or fulcrum, producing rotation about that point

the result of mass x acceleration

a body’s capacity to do work

the force with which a mass is attracted toward the center of the earth

A

created when a force is applied at some distance from an axis or fulcrum, producing rotation about that point

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18
Q

The center of gravity is the point at which __________.

lift is generated

all weight is concentrated

all aerodynamic forces are concentrated

elevator authority is lost

A

all weight is concentrated

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19
Q

Wing Loading is:

the aircraft weight divided by the sine of the wing dihedral

the ratio of the aircraft weight to the surface area of the wing

the ratio of the aircraft weight to the wing span

the ratio of the aircraft weight to the volume of the wing

A

the ratio of the aircraft weight to the surface area of the wing

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20
Q

The Mean Camber Line:

is a line drawn halfway between the wing root and the wing tip/

is the line drawn perpendicular to the aerodynamic center of the wing

is a line drawn halfway between the leading edge and trailing edge of the wing

is a line drawn halfway between the upper and lower surface of an airfoil.

A

is a line drawn halfway between the upper and lower surface of an airfoil.

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21
Q

The chord of an airfoil is defined as ___________.

an infinitely long line drawn through the leading and trailing edges of an airfoil

a measure of the wing along the chord line, from the leading edge to the trailing edge

the angle between the longitudinal axis and the horizon

the length of a wing

A

a measure of the wing along the chord line, from the leading edge to the trailing edge

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22
Q

Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?

F = ma

a = Fm

m = Fa

F = m/a

A

F = ma

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23
Q

The angle of attack of a wing is the angle between the wing’s cord and the horizon
True
False

A

False

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24
Q

The axis is which the aircraft nose moves left or right about the center of gravity
pitch
yaw
center
roll

A

yaw

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25
Q

The camber of an airfoil:

is the average distance between the cord and the mean camber line measured perpendicular to the cord

is expressed as a percentage of the wing surface area.

is the maximum distance between the cord and the mean camber line measured perpendicular to the cord

is the distance between the cord and the mean camber line measured at the aerodynamic center of the wind

A

is the maximum distance between the cord and the mean camber line measured perpendicular to the cord

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26
Q

Aspect Ratio of a wing is

the ratio of the wingspan to the average cord

the ratio of the average cord to the camber

the ratio of the wing surface area to the average cord

the ratio of the wing surface area to the wingspan

A

the ratio of the wingspan to the average cord

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27
Q

A _________ airfoil produces lift at zero degrees angle of attack.

symmetric

tapered

dihedral

positively cambered

A

positively cambered

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28
Q

What does sweeping a wing back do to CLMAX

Slightly decreases CLMAX and increases Stall AOA

Slightly increases CLMAX and increases Stall AOA

Slightly decreases CLMAX and decreases Stall AOA

Slightly increases CLMAX and decreases Stall AOA

A

Slightly decreases CLMAX and increases Stall AOA

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29
Q

Aspects of which two laws seem to contribute to the production of lift?

Ohm’s Law and the Heisenberg Uncertainty Principle

Bernoulli’s Law and Newton’s Third Law of Motion

Pascal’s Law and Bernoulli’s Law

General Gas Law and Newton’s Second Law of Motion

A

Bernoulli’s Law and Newton’s Third Law of Motion

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30
Q

Velocity and AOA are ____________ related in level flight
Directly
Not at all
Inversely

A

inversely

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31
Q

The AOA which produces CLMAX is called the:

Best rate of climb AOA

Stall AOA

Best Angle of Glide AOA

Best Angle of Climb AOA

A

Stall AOA

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32
Q

As the AOA increases, the center of lift ___________.

Moves rearward

Moves forward

Stays Stationary

A

moves forward

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33
Q

When an aircraft flies more slowly, more AOA is needed, when it flies faster less AOA is needed
true
false

A

true

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34
Q

L/DMAX is the point where .

drag is the greatest

the ratio of lift to drag is the greatest

the stall angle of attack is reached

lift is the greatest

A

the ratio of lift to drag is the greatest

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35
Q

Which factors are accounted by the Coefficient of Lift?

Velocity

Angle of Attack

Aspect Ratio

Camber

Surface area of the wing

Viscosity

Air Density

Compressibility

A

AOA
Velocity
Camber
Compressibility
Aspect Ratio

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36
Q

AOA is the most important factor in the CL and the easiest for the pilot to change
true
false

A

true

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37
Q

The Center of Pressure is the point on the wing where the vectors of lift and drag act
true
false

A

true

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38
Q

What are the factors that affect lift?

Compressibility

Air Density

Viscosity

Dihedral Angle

Mean Cord Length

Aspect Ratio

Angle of Attack

Surface area of the wings

Velocity

Camber

A

Compressibility
air density
viscosity
aspect ration
angle of attack
surface area of the wings
velocity
camber

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39
Q

Ground Effect __________.

Drastically increases lift available

Reduces the interference drag of the landing gear

Reduces the low pressure wake which causes form drag

Blocks the effect of Induced Drag

A

Blocks the effect of Induced Drag

40
Q

When does ground effect start becoming a factor?

50 feet AGL

one wingspan above the ground

two wingspans above the ground

100 feet AGL

A

one wingspan above the ground

41
Q

Drag that is produced simply due to the production of lift is called ________.

Interference Drag

Form Drag

Induced Drag

Viscous Drag

A

induced drag

42
Q

Parasite drag is ___________.

the component of drag associated with the production of lift

minimized by installing winglets, wingtip fuel tanks or missile rails

greatest at low airspeeds

made up of form, friction, and interference drag

A

made up of form, friction, and interference drag

43
Q

Streamlining shapes and increasing _________ are useful methods of reducing form drag.

Angle of Attack

Viscous Drag

Velocity

Frontal Area

A

Viscous Drag

44
Q

Total drag is composed of ____________.

upwash and downwash

form and interference drag

parasite and induced drag

thrust and lift

A

parasite and induced drag

45
Q

Which of these are true about L/D Max

  • Any movement away from L/D Max airspeed will increase total drag
  • L/D Max AOA produces minimum total drag
  • L/D Max AOA corresponds to the aircraft’s maximum speed
  • At L/D Max, induced and parasite drag are equal to each other.
  • The maximum amount of lift that an aircraft can produce occurs at L/D Max AOA
A

Any movement away from L/D Max airspeed will increase total drag

L/D Max AOA produces minimum total drag

At L/D Max, induced and parasite drag are equal to each other.

46
Q

Drag that is created by airflow separating from the surface of an object and the low pressure wake that is created by that separation is called __________.

Interference Drag

Form Drag

Viscous Drag

Induced Drag

A

form drag

47
Q

Drag that is created by mixing airstreams between components is called _________.

Form Drag

Interference Drag

Viscous Drag

Induced Drag

A

Interference Drag

48
Q

An increase in weight or altitude will ____________ L/D Max airspeed but will ___________ L/D Max AOA.

decrease / not affect

decrease / increase

increase / not affect

increase / decrease

A

increase / not affect

49
Q

Accelerating the air that surrounds a moving object requires force, thus creating drag. This is an example of _________ drag.

Form Drag

Interference Drag

Induced Drag

Viscous Drag

A

Viscous Drag

50
Q

In a jet aircraft, as velocity increases, thrust available _________.

Decreases

Stays the same

Increases

A

stays the same

51
Q

With a variable pitch prop, what instrument in the cockpit is used to represent power?

Prop Pitch

Engine Exhaust Temperature

Shaft Torque

PRM

A

shaft torque

52
Q

An increase in aircraft weight will shift the thrust required and power required curves

down and to the right

up and to the left

down and to the left

up and to the right

A

up and to the right

53
Q

A thrust required curved can be use for various, weights, altitudes and configurations.
true
false

A

false

54
Q

Lowering an aircraft’s landing gear will shift the thrust required and power required curves

up and to the right

straight up

up and to the left

straight down

A

straight up

55
Q

What are the five basic types of jet engines?

Centrifugal Flow Engine

Water Injected Engine

Ramjet Engine

Rocket Assisted Engine

Radial Flow Engine

Turbofan Engine

Circular Flow Engine

Axial-Centrifugal Compressor Engine

A
  • Axial-Centrifugal Compressor Engine
  • Centrifugal Flow Engine
  • Turbofan Engine
  • Radial Flow Engine
  • Ramjet Engine
56
Q

In equilibrium flight, thrust must ____________ drag.

be less than

be equal to

be greater than

A

be equal to

57
Q

Torque and P-Factor both affect how propeller aircraft fly. What effect to each have on aircraft

The both create a yawing motion

Torque creates a rolling motion, P-Factor creates a yawing motion.

They both create a rolling motion

Torque creates a yawing motion, P-Factor creates a rolling motion

A

Torque creates a rolling motion, p-factor creates a yawing motion

58
Q

For a propeller driven aircraft, max excess power occurs at

L/D Max airspeed

A speed less than L/D Max

A speed greater than L/D max

A

L/D max airspeed

59
Q

For a jet, power available increases linearly with an increase of velocity.
true
false

A

true

60
Q

Since aircraft designers wish to minimize the effects of P-Factor, they align the thrust axis with the relative wind for cruise airspeeds. Thus, P-Factor will be most prevalent at AOAs significantly different from cruise AOA.
true
false

A

true

61
Q

How do you locate L/D Max for a propeller driven aircraft on a Power Required (Power vs. Velocity) Curve

Draw a straight line starting at the origin of the graph and tangent to the curve. The tangent point is L/D Max.

L/D Max occurs where the slope of the graph is equal to one

L/D Max occurs five knots slower than the lowest point on the graph

L/D Max is the lowest point on the graph

A

Draw a straight line starting at the origin of the graph and tangent to the curve. The tangent point is L/D Max.

62
Q

For a propeller driven aircraft, max excess thrust occurs at

L/D Max Airspeed

A speed greater than L/D Max

a speed less than L/D Max

A

a speed less than L/D Max

63
Q

Output from an engine in a propeller driven aircraft is called

Shaft Horsepower

Centrifugal Horsepower

Brake Horsepower

Thrust Horsepower

A

Shaft Horsepower

64
Q

Slipstream swirl is the most noticeable at

high power settings at high airspeed

low power settings at low airspeed

high power settings at low airspeed

low power settings at high airspeed

A

high power settings at low airspeed

65
Q

Maximum power available occurs at the full throttle setting.
true
fasle

A

true

66
Q

For both jet and propeller driven aircraft, as air density decreases, thrust ________.

Increases

Stays the same

Decreases

A

Decresases

67
Q

Output from a propeller is called

Shaft Horsepower

Brake Horsepower

Thrust Horsepower

Centrifugal Horsepower

A

Thrust Horsepower

68
Q

Propeller Efficiency is determined by Thrust Horsepower divided by Shaft Horsepower
true
false

A

true

69
Q

For a turbojet, max excess thrust occurs at _________________.

At a speed less than L/D Max

At a speed greater than L/D Max

L/D Max Airspeed

A

L/D Max Airspeed

70
Q

In a propeller driven airplane, as velocity increases, thrust available ______.

Decreases

Stays the same

Increases

A

decreases

71
Q

For a turbojet aircraft, max excess power occurs at

L/D Max airspeed

A speed greater than L/D Max

A speed less than L/D Max

A

A speed greater than L/D Max

72
Q

Power on stall speed will be _______________ power off stall speed
faster than

the same as

lower than

A

lower than

73
Q

The only reason an aircraft stalls is because

The only reason an aircraft stalls is because

the wings have exceeded the stalling pitch angle

the aircraft has slowed below Vstall

Thrust required exceeds thrust available

the wings have exceeded the stalling angle of attack

A

the wings have exceeded the stalling angle of attack

74
Q

What is the only thing that needs to be done to recover from a stall?

What is the only thing that needs to be done to recover from a stall?

Increase thrust available to over thrust required

Lower the aircraft’s nose below the horizon

Decrease the AOA below the stalling angle of attack

Increase the aircraft’s speed to greater than Vstall

A

Decrease the AOA below the stalling angle of attack

75
Q

The slotted flap is more advantageous than a plain flap because air passing through the slot aids in boundary layer control
true
false

A

true

76
Q

Different things can be done to the design to a wing to give it good stall characteristics. The most common of these techniques are

Different things can be done to the design to a wing to give it good stall characteristics. The most common of these techniques are

Geometric wing twist

Installation of a stall strip

Installation of vortex generators

Installation of a wing fence

Aerodynamic wing twist

A

Aerodynamic wing twist
Geometric wing twist
Installation of a stall strip

77
Q

The most desirable stall pattern of a wing is one where the wing starts to stall at the wingtip and moves inboard.
true
false

A

false

78
Q

Most slats increase lift by increasing the wing’s camber
true
false

A

false

79
Q

Swept wings are used on high speed aircraft because they reduce drag and allow the aircraft to fly at higher mach numbers. Swept wings stall at the root first and progresses rapidly outward across the rest of the wing.
true
false

A

false

80
Q

When flaps are lowered, the pilot should

raise the nose due to the increase drag of the flaps

lower the nose due to the increased drag of the flaps

attempt to keep his flight attitude the same

lower the nose to keep the increase of lift from ballooning the aircraft

A

lower the nose to keep the increase of lift from ballooning the aircraft

81
Q

Fowler flaps are very effective high lift devices because

they increase the camber of the wing

They increase the aspect ratio of the wing

The have several slots so they aid in boundary layer control

since they move aft, they also increase the surface area of the wing

A

The have several slots so they aid in boundary layer control

since they move aft, they also increase the surface area of the wing
they increase the camber of the wing

82
Q

As a stall progresses, the _________ lose control effectiveness first, followed by the ________ and then finally the _________.

ailerons, rudder, elevators

rudder, ailerons, elevators

elevator, ailerons, rudder

ailerons, elevators, rudder

A

ailerons, elevators, rudder

83
Q

The two common types of high lift devices

Increase camber

Delay boundary layer separation

Increase the angle of attack

Increase the aspect ratio

A

Increase camber

Delay boundary layer separation

84
Q

Rectangular wings are limited to low speed, light weight construction where simplicity of construction and good stall characteristics are the predominant requirements
true
false

A

true

85
Q

Erect spins are either unaccelerated or accelerated. What control input will make a spin unaccelerated?

Rudder in the direction of spin

Full forward stick/yolk

Full aft stick/yolk

Ailerons against the direction of spin

A

Full aft stick/yolk

86
Q

How can you tell the difference between a spin and a spiral?

Airspeed

Roll rate

Rate of descent

Pitch attitude

A

Airspeed

87
Q

It is impossible for an aircraft to enter an inverted spin

True

False

A

False

88
Q

What two things do you need for a spin

The aircraft’s CG must be in the aft half of the flight envelope

The elevator must be trimmed nose down

A stalled aircraft

Some sort of yawing force must be present

A

A stalled aircraft

Some sort of yawing force must be present

89
Q

A spin is an aggravated stall that results in autorotation
True
False

A

True

90
Q

Slow activation of the elevators during the spin allows the spin to accelerate. This makes for a much easier and smoother recovery
true
false

A

false

91
Q

What keeps the spin goin?

The P-Factor from the engine

Due to the yawing motion, the wings are not symmetrically stalled.

Gyroscopic precession caused by the engine or prop

Any difference in wing fuel quantity

A

Due to the yawing motion, the wings are not symmetrically stalled.

92
Q

Poststall gyrations are dependent upon an aircraft’s _________.

weight

airspeed

CG

G loa

A

airspeed

93
Q

An aircraft’s spin axis is always located in the center of the fuselage at the 50% cord line.
true
false

A

false

94
Q

What is usually the most effective control for stopping the autorotation

Rudder

Elevators

Aileron

A

Rudder

95
Q
A

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