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AT 106 > Exam 2 > Flashcards

Exam 2 Flashcards

1
Q

what are the two aircraft engine types

A

Reciprocating
turbo powered

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2
Q

Heat engines

A

utilize heat energy to produce the power for propulsion

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3
Q

Kinetic energy

A

energy in motion

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4
Q

potential energy

A

energy of position or stored energy

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5
Q

Normal category G rating

A

+3.8
-1.52

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6
Q

Utility category G rating

A

+4.4
-1.76

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7
Q

Acrobatic Category G rating

A

+6
-3

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8
Q

Positive G Loads

A

pull back on the control wheel stick
centrifugal force acts in the same direction as weight
makes you feel heavier

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9
Q

Negative G load

A

Push the stick or control wheel forward
centrifugal force acts in the opposite direction as weight- an upward force on the aircraft
makes you feel lighter

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10
Q

Load factor

A

ratio of the total load supported by the wing compared to the weight of the aircraft

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11
Q

load factor increases as

A

bank increases

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12
Q

what are the two kinds of stability

A

static
dynamic

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13
Q

the vertical stabilizer and swept back wings help maintain _____ stability

A

yaw

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14
Q

Camber on the bottom of the tail uses Bernoulli Effect on the bottom of the horizontal stabilizer, and creates ____

A

negative lift

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15
Q

what are the 6 flap types

A

basic
plain
split
slotted
fowler
slotted fowler

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16
Q

droop leading edge

A

lower the AOA and gives the wing a higher camber s the air sees it

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17
Q

Kreuger Flaps

A

another leading edge device
lower the AOA, increase camber and more rounded leading edge

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18
Q

effective aspect ratio

A

gives the wings characteristics of a higher aspect ratio
high aspect ratio wings produce less drag

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19
Q

things to do to prevent wingtip vortices (better aspect ratio)

A

drooped wing tips
end plates
fuel tanks
missile launchers
winglets/ sharklets
joined wings
forward swept wings

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20
Q

Leading edge slat

A

slotted leading edge slat

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21
Q

better lift/ drag ratio high wing

A

better lateral stability
shorter landing distance

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22
Q

better lift/ drag ratio low wing

A

easier to build strong landing gear support
better roll maneuverability
shorter take off distance

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23
Q

which wing configuration is most susceptibal to ground effect

A

the one with the wings closest to the ground

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24
Q

Horizontal stabilizer Tee Tail advantages

A

keeps horizontal stabilizer and rudder out of the main wing downwash

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25
Q

horizontal stabilizer tee tail disadvantage

A

vertical stabilizer must be larger and heavier

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26
Q

Horizontal Stabilizer: Vee Tail advantages

A

decrease interference drag by eliminating the number of acute angles, typically lighter and less wetted surface, drag is reduced, increase stealth

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27
Q

Vertical Stabilizer: Vee tail diadvantages

A

require a much more complex control system, required to be structurally more robust, control forces required for operating the ruddervators are higher

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28
Q

different placement of vertical stabilizer why?

A

fuselage tends to block the airflow to a normal single c=vertical stabilizer and rudder
fighters often have 2 tails for this reason, more control

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29
Q

flying wires BiPlane

A

transmit the left back to the fuselage

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30
Q

landing wires BiPlane

A

transmit the downward impact of landing, or negative G loads, on the wings back to the fuselage

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31
Q

Interplane struts

A

transmits the lift loads and landing loads between the top and bottom wings

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32
Q

Cabane struts BiPlane

A

support the top section of wing above the fuselage and transmits the lift loads of the wing roots to the fuselage

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33
Q

The Center Section BiPlane

A

an airfoil-shaped section above the fuselage to which the upper wings attach

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34
Q

Interplane interference

A

airfoils flying in proximity reduce differential in psi

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35
Q

the gap between the BiPlane wings

A

the distance between the top chord and the bottom chord of the 2 wings. must be 1 chord length

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36
Q

Interplane interference affected is by

A

Decalage

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37
Q

Decalage on a fixed-wing aircraft is

A

the angle of difference between the upper and lower wings of a biplane

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38
Q

Tandem Wing

A

both wings lift up and there is no horizontal stabilizer pulling down
very limited center of gravity range
very limited center of gravity

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39
Q

what is a canard wing

A

a special type of tandem wing
canard should carry no more than 25% of the total weight
canard wing stalls before the other wing
very lfit efficient

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40
Q

Flying wing

A

drag is greatly reduced,
stabillity is hard
have to worry about center of gravity moving left and right

41
Q

what did wing airplane need

A

spit rudders
elevons
this gave us much more stability and replaced out tail

42
Q

what are ruddervators

A

Vee tails

43
Q

____________ does not apply at supersonic speeds because____

A

Bernoulli’s principle
his principle assumes that air is not compressible and at super sonic speeds we need to understand that air is a compressible fluid

44
Q

as airflow approaches sonic speeds, air becomes

A

a compressible fuid

45
Q

why does the speed of sound change at altitudes

A

it changes based on
cold molecules move slower
standard day 760 mph

46
Q

sonic boom

A

a loud sound kind of like an explosion
caused byyour plane moving air out of its way and it following the plane
happens when you are faster than the speed of sound

47
Q

Mach number

A

the speed of the aircraft in relation to the speed of sound

48
Q

mach calculation

A

true speed of the aircraft/ speed of sound

49
Q

subsonic

A

any region below the transonic region or below the critical Mach number

50
Q

Transonic

A

begins with teh first evidence fo localized sonic or supersonic airflows and begins at the critical mach number. Transonic region ends when all flows around the aircraft are fully supsonic

51
Q

Sonic

A

right at the speed of sound

52
Q

supersonic

A

any speed faster that the speed of sound

53
Q

hypersonic

A

any speed above mach 5. Plasma effects begin to affect airflows

54
Q

the transonic region begins with

A

the first evidence of sonic or supersonic flow around the aircraft

55
Q

transonic flow creates

A

the most drag on a high speed aircraft

56
Q

Mcrit

A

when some flows are supersonic and some are subsonic you are flying in the
when you enter transonic regime

57
Q

shock waves

A

air at supersonic speeds is compressed because the air no longer has enough energy to be able to get out of the way of the aircraft, the air molecules get shoved together and compressed, the air compresses, builds up, and sticks to the wing

58
Q

two types of shock waves

A

normal
oblique

59
Q

split flap

A

adds some lift and drag

60
Q

slotted flap

A

lift is increased greatly
drag slightly

61
Q

Fowler Flap

A

increases drag

62
Q

Normal Shock Wave

A

perpendicualr to flow direction
shock wave absorbs energy from the air and causes tremendous drag

63
Q

Oblique shock wave

A

wave consumes some of the energy from the air and creates some drag

64
Q

how is lift made

A

lift is generated only by the angle of attack

65
Q

how does design effect shock waves

A

The flatter upper camber will keep the airspeeds across the wing lower than that of a normal cambered wing
Lowest pressure orces on a supercritical wing are also concentrated around the highest camber

66
Q

how does thrust, drag, lift, and weight work together in a helicopter

A

thrust and lift work upwards together
weight and drag work downwards together

67
Q

Collective stick

A

moves the helicopter vertically
changes the angle of attack of all blades at the same time
pulling up gives all blades a larger angle of attack so they take bigger bites of air

68
Q

cyclic operation

A

controls movement forward, backward, etc
it changes the blade pitch at only one part of its rotating cycle which tips the rotor disk forward and moves the helicopter
when pushing forward the blade in the back will always have the higher angle of attack which will move you forward

69
Q

helicopter rotors run at a constant ___ in flight

A

RPM

70
Q

with no centrifugal force from rotation to hold them straight the rotors will ______ when they are not spinning

A

droop

71
Q

the spinning rotor blades generate a _____ that keeps the blades stretched out straight and prevents the blades from folding up or breaking

A

centrifugal force

72
Q

Coneing

A

blades pull up or cone when they are spinning and put under a lift load

73
Q

what control the direction a helicopter is facing

A

anti-toque pedals

74
Q

what is the tail rotor controlled by

A

foot pedals
a lot like the rudder of the plane

75
Q

what are foot pedals also called

A

anti-torque pedals

76
Q

the tail rotor also counteracts the

A

torque of the spinning main rotor blade

77
Q

what happens if the tail rotor quits

A

the helicopter spins around in a circle in the opposite the direction of the main rotor

78
Q

what is something we can put on a tail rotor

A

Fenestron
it is a device that covers the tail rotor

79
Q

on the fenestron for aerodynamic efficiency, the shroud is

A

rounded at the upstream air intake and flared downstream
good for small and medium helicopter

80
Q

what is the best thing about fenestron

A

greatly reduces injuries due to tpeople running into tail rotor, and reduces accident where tail rotors strike objects

81
Q

eliminating tail rotors

A

greatly reduces noise and improves safety
only works on small helicopters

82
Q

NOTAR-because torqu to fuselage changes as main rotor blade pitch changes

A

the engine runs at a constant RPM
a fan with variable pitch blades is put in front of the tail boom to force air into the boom

83
Q

NOTAR- as more main rotor pitch is used and more anti-torque is needed

A

the fan changes pitch automatically increasing the flow of air out through the slot in the starbourd side of the tail

84
Q

control surface

A

movable airfoil on any surface

85
Q

primary flight controls

A

elevator, rudder, ailerons

86
Q

Secondary flight controls

A

modify the effects of the primary flight controls or air flows

87
Q

Primary flight control airleron

A

controls roll
longitudinal rotation about the longitudinal axis
lateral stability

88
Q

Primary flight control: elevator

A

controls pitch
rotation about the lateral axis
longitudinal stability

89
Q

Primary flight control: rudder

A

controls yaw
rotation about the vertical axis
directional stability

90
Q

how do ailerons work

A

turn the yoke in the direction you want to go
the airleron in the direction you turned will go up and the opposite will go down
the down airleron will create more lift creating a turning tendency

91
Q

Slipping turn

A

need to add more rudder

92
Q

skidding turn

A

need to add less rudder

93
Q

adverse yaw how do you fix it

A

differential ailerons
the aircraft may roll one way but directionally turn the opposite as a result an imbalance of drag at the wingtips between the left and right wing
differential aileron fix this, the up aileron will raise more so that it catches more air than the down aileron which will equal out the drag

94
Q

Flaps

A

a high light/high drag device, improve the lifting ability

95
Q

Slats

A

a high lift device typically found on jets, mounted don’t eh leading edge, change the camber and curvature of the wing to improve lifting ability at slower speeds

96
Q

Secondary flight controls: trim tabs

A

used to get flight control setting jsut right, little tabs often found on the rudder, elevator, and airleron

97
Q

Secondary flgiht controls: flgiht spoilers

A

kill lift, they are not speed breaks, mounted on the upper surface of the wing and when extended increase drag and decrease lift by disrupting airflow

98
Q

Secondary flight controls: ground spoilers

A

maximinze wheel brake efficiency
flight spoilers are often ground spoilers

99
Q

Secondary flgiht controls: speed brakes

A

not spoilers, used to create drag to slow the airplane, mostly fuselage mounted panels

AT 106 (4 decks)

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