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Aero 1 > Basic Theory > Flashcards

Basic Theory Flashcards

1
Q

Scalar

A

quantity that represents only magnitude

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2
Q

Vector

A

quantity that represents magnitude and direction

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3
Q

Displacement (s)

A

distance and direction of a body’s movement

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4
Q

Velocity (V)

A

speed and direction of a bod’s motion, the rate of change of position

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5
Q

Speed

A

scalar equal to the magnitude of the velocity vector

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6
Q

Acceleration (a)

A

rate and direction of a body’s change of velocity

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7
Q

Force (F)

A

push or pull exerted on a body

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8
Q

Mass (m)

A

quantity of molecular material that comprises an object

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9
Q

Volume (v)

A

amount of space occupied by an object

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10
Q

Density (ρ)

A

mass per unit volume

ρ = mass/volume

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11
Q

Weight (W)

A

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

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12
Q

Force (F)

A

mass times acceleration

F= m (x) a

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13
Q

Moment (M)

A

created when a force is applied at some distance from an axis or fulcrum, tends to produce rotation about that point. A vector quantity equal to Force time distance from the point of rotation that is perpendicular to the force.

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14
Q

Work (W)

A

scalar quantity

W= F (x) s

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15
Q

Power (P)

A

rate of doing work or work done per unit of time

P = W/t

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16
Q

Energy

A

scalar measure of a body’s capacity to do work

TE= PE + KE

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17
Q

Potential Energy

A

ability of a body to do work because of its position or state of being. Function of mass (m), gravity (g), and height (h).
PE= weight (x) height = mgh

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18
Q

Kinetic energy

A

ability of a body to do work b/c of its motion. Funcition of mass (m) and velocity (V).
KE = 1/2mV ²

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19
Q

Work

A

changes position to give potential energy or motion to give kinetic energy

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20
Q

Newton’s First Law

A

Law of Equilibrium
“Body at rest tends to remain at rest and a body in motion tends to remain in motion in a straight line at a constant velocity unless acted upon by some unbalance force

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21
Q

Equilibrium

A

absence of acceleration, either linear or angular

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22
Q

Equilibrium flight

A

exists when the sum of all forces and the sum of all moments around the center of gravity are equal to zero. thrust, drag, lift and weight cancel each other out

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23
Q

Trimmed flight

A

exists when the sum of all moments around the center of gravity is equal to zero. Sum of forces may not be equal to zero. DOES NOT NEED TO BE IN STRAIGHT AND LEVEL FLIGHT

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24
Q

Newton’s Second Law of Motion

A

Law of Acceleration
“An unbalanced force (F) acting on a body produces an acceleration (a) in the direction of the force that is directly proportional to the mass (m) of the body”
a=F/m a= (Vout (-) Vin)/time

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25
Q

Newton’s Third Law of Motion

A

Law of Interaction
“For every action, there is an equal and opposite reaction; the forces of two bodies on each other are always equal and are directed in opposite directions

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26
Q

Static pressure (Ps)

A

the pressure that particles of air exert on adjacent bodies

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27
Q

Air density (ρ)

A

total mass of air particles per unit of volume. Decreases with an increase in altitude

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28
Q

Temperature (T)

A

measure of the average random kinetic energy of air particles

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29
Q

Average lapse rate

A

Linear temperature decrease for each 1000 ft increase in altitude. 2°C (3.57°F) per 1000 ft up to 36,000 ft

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30
Q

Humidity

A

amount of water vapor in the air

as humidity inc, air density dec

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31
Q

Viscosity (µ)

A

measure of the air’s resistance to flow and shearing

inc as temp inc

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32
Q

Local speed of sound

A

rate at which sound waves travel thru a particular air mass

dependent only on the temperature of the air

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33
Q

Standard atmosphere

A

set of reference conditions giving representative values of air properties as a function of altitude

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34
Q

General Gas Law

A

set the relationship b/w pressure (P), density (ρ), and temperature (T)
P=ρRT

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35
Q

Altitude

A

defined as the geometric height above agiven plane of reference

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36
Q

True altitude

A

actual height above sea level

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37
Q

Pressure altitude (PA)

A

height above the standard datum plane (22.92 in. Hg)

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38
Q

Density altitude (DA)

A

altitude in the standard atmosphere where the air density is equal to local air density. Found by correcting pressure altitude for temp and humidity.
Predictor of aircraft performance.

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39
Q

Steady airflow

A

Exists if at every point in the airflow static pressure, density, temp and velocity remain constant over time. Particles do not cross streamlines.

40
Q

Streamtube

A

collection of many adjacent streamlines

41
Q

Continuity Equation (ṁ)

A

Amount of mass passing any point in the streamtube

ṁ= ρAV

42
Q

Continuity Equation

A 
ρ1A1V1 = ρ2A2V2
A1V1= A2V2
43
Q

Static pressure (ps)

A

the pressure particles of air exert on adjacent bodies

44
Q

Dynamic pressure (q)

A

measure of impact pressure of a large group of air molecules moving together
q= (1/2)ρV ²

45
Q

Total pressure (H)

A

sum of static and dynamic pressure
inc in static results in dec in dynamic, and vice versa
H = ps + (1/2)ρV ²

46
Q

Bernoulli’s equation

A

H= ps + q

47
Q

Airspeed Measurement equation

A

q= H (-) Ps

48
Q

pitot static system

A

consists of pitot tube that senses total pressure (H), static port that senses static pressure (Ps) and differential pressure gauge

49
Q

pitot tubes used for…

A

measuring total pressure

50
Q

static port measures…

A

static pressure

51
Q

Indicated airspeed (IAS)

A

actual instrument indication of dynamic pressure the airplane is exposed to

52
Q

Instrument error

A

caused by indicator errors and errors due to the pysical location of the static port

53
Q

Calibrated airspeed (CAS)

A

indicated airspeed corrected for instrument error

54
Q

compressibility error

A

caused by ram effect of air in pitot tube resulting in higher than normal airspeed indications

55
Q

Equivalent airspeed (EAS)

A

true airspeed at sea level on a standard day that produces the same dynamic pressure as the actual flight condition

56
Q

Pitot tubes

A

used to measure total pressure

57
Q

Static port

A

measures static pressure

58
Q

Indicated airspeed (IAS)

A

actual instrument indication of the dynamic pressure the plane is exposed to during flight

59
Q

instrument error

A

caused by the indicator errors and errors due to the physical location of the static port on the aircraft

60
Q

True airspeed

A

actual velocity at which an airplane moves through an air mass

61
Q

Ground speed

A

airplane’s actual speed over the ground
GS= TAS (-) HEADWIND
GS= TAS (+) TAILWIND

62
Q

aircraft

A

any device used or intended to be used for flight in the air

63
Q

airplane

A

mechanically driven fixed-wing aircraft, heavier than air, which is supported by the dynamic reaction of the air against its wings

64
Q

fuselage

A

basic structure of the airplane to which all other components are attached

65
Q

truss

A

consists of metal/wooden frame over which a light skin is stretched. truss supports entire load

66
Q

full monocoque

A

skin shell that supports entire load

67
Q

semi-monocoque

A

modified monocoque with skin, frame members, and stringers that share the load

68
Q

wing

A

airfoil attached to the fuselage designed to produce lift

69
Q

ailerons

A

attached to wing to control roll

70
Q

empennage

A

assembly of stabilizing and control surfaces on the tail of an airplane
greatest stabilizing force

71
Q

elevators

A

attached to horizontal stabilizer to control pitch

72
Q

landing gear

A

permits ground taxi operation and absorbs shock encountered during takeoff and landing

73
Q

engine

A

provides thrust necessary for powered flight

74
Q

mean camber line (MCL)

A

line halfway b/w upper and lower surface of an airfoil

75
Q

chord line

A

infinite line that passes thru leading and trailing edges of an airfoil

76
Q

root chord (cr)

A

chord at the wing centerline

77
Q

tip chord (ct)

A

chord at wing tip

78
Q

average chord (c)

A

avg of every chord from wing root to wingtip

79
Q

camber

A

ma distance b/w mean camber line and chord line

measured perpendicular to chord line

80
Q

Aerodynamic center

A

point along chord line around which all changes in the aerodynamic force take place

81
Q

Wingspan (b)

A

length of wing measured wingtip to wingtip

82
Q

Wing area (S)

A

apparent surface area of a wing from wingtip to wingtip

S=bc (wing area= wingspan x avg. chord

83
Q

Taper

A

reduction in chord of an airfoil from root to tip

84
Q

sweep angle

A

angle b/w lateral axis and line drawn 25% aft of leading edge

85
Q

Aspect ratio (AR)

A

ratio of wingspan to avg chord

AR= b/c

86
Q

Wing loading (WL)

A

ratio of plane’s weight to surface area of wings

WL=W/S

87
Q

Angle of incidence

A

angle b/w plane’s longitudinal axis and chord line of wing

88
Q

Dihedral angle

A

angle b/w spanwise inclination of wing and lateral axis (upward slope of wing when viewed from front)

89
Q

Anhedral angle

A

negative diheral angle

90
Q

Pitch attitude

A

angle b/w plane’s longitudinal axis and the horizon

91
Q

flight path

A

path of plane described by center of gravity as it moves thru an airmass

92
Q

Relative wind

A

airflow the plane experiences as it moves thru the air

93
Q

angle of attack (AOA)

A

angle b/w relative wind and chord line of airfoil

94
Q

Spanwise flow

A

airflow that travels along span of wing, parallel to leading edge
produces no lift

95
Q

Chordwise flow

A

air flowing at right angle to leading edge of airfoil

only airflow that produces lift

Aero 1 (1 decks)

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