Aerodynamics (AA1290) Flashcards

1
Q

What is center of gravity (Cg)?

A

-“3 axes intersect and all weight is concentrated”

-the point where the roll, yaw, and pitch axes intersect and from which all axes movements are measured
-the point where all weight is considered to be concentrated

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2
Q

What is aerodynamic center (AC)?

A

-“changes in lift occur”

-the point along the chord line of the wing, approx. 23-27% from the leading edge, around which the wing forces act through and all changes in lift effectively occur

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3
Q

What is Angle of Attack?

A

Angle between the wing’s chord line and the relative wind

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4
Q

What are the 4 primary forces acting on an aircraft?

A

Lift, Weight, Thrust, and Drag

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5
Q

How does weight act on the aircraft?

A

Weight acts through the aircraft’s CG towards the Earth (always perpendicular to the surface regardless of attitude)

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6
Q

What is lift and how does it act?

A

-Lift opposes the downward force of weight and acts perpendicular to the flight path
-Lift can be in any direction (not always upwards) based on aircraft attitude
-Wings generate most of the lift, but the horizontal stab and fuselage also generate some

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7
Q

What is drag and how is it formed?

A

-Drag is the rearward force that opposes thrust
-Drag results from the disruption of airflow and the production of lift

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8
Q

What is thrust?

A

-thrust is the acceleration and reaction force described in Newton’s 3rd law
-forward force that opposes drag
-assume thrust acts parallel to the longitudinal axis in the T-38C

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9
Q

What is aerodynamic force (AF)?

A

the combined effect of lift and drag in a single net force

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10
Q

Where does aerodynamic force come from and where does it usually point?

A

-aerodynamic force is the result of pressure and friction distribution over the wing
-direction and size varies, but generally points up and to the rear of the aircraft

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11
Q

When the aircraft is in stable, unaccelerated flight, the forces are?

A

balanced

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12
Q

What happens to the 4 forces in a turn?

A

-Lift: is being shared in a horizontal and vertical component (which decreases the amount available to oppose weight)

-Weight: remains the same

-Drag: ultimately increases b/c AoA must be increased to compensate for the decreasing vertical lift

-Thrust: must increase proportional to the turn to overcome the additional drag

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13
Q

What is the only force that does not change in size or direction when a climb is initiated?

A

Weight

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14
Q

How does the 4 forces get affected in a climb?

A

In a stabilized climb, lift is less than weight and thrust must increase to overcome

W: weight is now not only acting downward, but has a rearward component with drag (WD)

L: lift is still equal to the downward force of weight (WL)

T: Thrust must increase to overcome the addition of Wd

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15
Q

The steeper the climb angle, the (more/less) lift is required to maintain balanced flight.

A

Less lift.
It is the thrust force that increases to support the drag portion of weight (WD) that is not being supported by lift (L = WL)

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16
Q

What are the two components of weight in a power-on descent?

A

WL and WT (the thrust component of weight)

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17
Q

How are the 4 forces balanced in a power-on descent?

A

W: 2 components; WL and WT
L: is still opposing WL
D: equals T and WT
T: MUST be less than drag

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18
Q

In a power-on descent, ___ must be less than ____

A

thrust is less than drag (b/c D = T + WT)

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19
Q

In a wings-level, constant airspeed climb, lift is ____ weight

A

less than

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20
Q

In the flow of incompressible fluid, the sum of static pressure and dynamic pressure is ____

A

constant (which is why pressure and velocity are inversely related)

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21
Q

What are the two key factors that the pilot can control in the lift equation?

A

Velocity and Angle of Attack

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22
Q

What is the simplified “pilot’s lift equation”?

A

Lift = V^2 x AoA

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23
Q

What is stall angle of attack?

A

the AoA associated with the lift limit of the wing at a given airspeed (beyond this point results in a decrease in CL)

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24
Q

The aircraft always stalls at the same ___ regardless of ____

A

AoA, regardless of airspeed

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25
Q

What is stall speed (Vs)?

A

the minimum airspeed under a given set of conditions that the aircraft will stall (this speed varies)

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26
Q

What is the minimum airspeed to maintain straight-and-level flight?

A

1-G stall speed

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27
Q

How does weight vary stall speed?

A

The greater the weight, the greater lift required to maintain level flight, therefore STALL SPEED INCREASES

(same reason why approach speeds increase with weight)

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28
Q

How does flap configuration change stall speed?

A

Lowering the flaps DECREASES stall speed

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29
Q

How does bank angle affect stall speed?

A

Increasing bank angle = INCREASING STALL SPEED

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30
Q

How does altitude affect stall speed?

A

an increase in altitude results in a higher stall TAS, however there is very little (if any) change to the stall CAS

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31
Q

How does stall speed change with and without thrust?

A

Stall speed with full thrust is somewhat lower than idle power stall speed

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32
Q

In general, what effect does an increase in AOA have on lift if CAS is kept constant?

A

Lift increases

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33
Q

What effect does lowering the flaps have on the 1-G level flight stall speed of the T-38?

A

decreases the stall speed

34
Q

What effect does increasing bank angle have on the level flight stall speed of the T-38?

A

Increases the stall speed

35
Q

What is parasite drag?

A

drag not associated with the production of lift

36
Q

What are the three main types of parasite drag?

A

Interference, skin friction, and form drag

37
Q

What is form drag?

A

parasite drag generated by the aircraft due to its shape

38
Q

What is interference drag?

A

parasite drag from the intersection of airstreams that cause eddy currents, turbulences, or restricts smooth airflow

39
Q

What is skin friction drag?

A

parasite drag that is the aerodynamic resistance due to the contact of moving air over the aircraft surface (creates a boundary layer of essentially motionless air)

40
Q

At transonic speeds and above, a fourth type of parasite drag called ____ is encountered

41
Q

Parasite drag varies with ____

A

velocity; as velocity increases so does parasite drag

42
Q

What is induced drag?

A

drag caused by the production of lift

43
Q

Induced drag varies with ____

A

AOA (NOT airspeed)…the induced drag for a 4-G maneuver at 400 KIAS is greater than the same maneuver at 3-G b/c of the greater AOA

44
Q

How does induced drag change with weight?

A

the heavier the aircraft, the greater lift is required, therefore induced drag also increases

45
Q

How does induced drag change with bank angle?

A

Induced drag increases with bank angle

46
Q

What is total drag?

A

The sum of parasite and induced drag

47
Q

What is L/D max in the T-38C?

A

230 KCAS plus 1 KCAS for every 100 pounds of fuel

48
Q

An increase in level-flight airspeed causes induced drag to ____

49
Q

What is the relationship between parasite drag and aircraft velocity? (Linear, exponential, negative, etc)

A

Parasite drag increases exponentially with velocity (CAS)

50
Q

How does the parasite drag curve change by lowering the gear?

A

Lowering the gear increased parasite drag which creates a steeper curve with an increase in airspeed

51
Q

How does the drag due to thrust curve change with increasing weight?

A

an increase in weight causes an increase in L/D Max CAS. Total drag at the corresponding L/D Max also increases. Thus, we expect the left side of the total drag curve to shift upwards

52
Q

What is thrust required (TR)? What must it equal?

A

the thrust needed to maintain steady, unaccelerated level flight. Thrust required must equal total drag (DT)

53
Q

What is thrust available (TA)

A

the thrust the engines produce at a given throttle setting, velocity, and density

54
Q

What is assumed about the available thrust of a turbojet?

A

it is assumed to be a straight line

55
Q

What happens to thrust available with temperature?

A

As the temperature increases, the TA decreases

56
Q

How does thrust available vary with altitude?

A

Increasing altitude has less dense air, which decreases the mass flow rate and TA.

The change in pressure altitude has a greater effect on air density than temperature (which is why performance decreases with altitude)

57
Q

What does absolute ceiling mean?

A

the point at which the aircraft reaches an altitude where the maximum TA equals the minimum TR

58
Q

Where on the graph is the maximum speed the aircraft can obtain in level flight?

A

the intersection of the TR curve and maximum TA line

59
Q

What is the lock point?

A

the minimum airspeed at which an airspeed can maintain level flight for that power setting

60
Q

Where is the lock point on the TA vs TR chart?

A

the first intersection of TA and TR

61
Q

Where does the maximum amount of excess thrust occur at?

A

L/D Max (the lowest point on the TR curve)

62
Q

What is the region of normal command vs. the region of reverse command?

A

normal command - greater than L/D max where increasing power setting increases airspeed

reverse command - less than L/D max where a higher power setting is required to fly a slower speed

63
Q

Which combination of pressure altitude and temperature produces the most thrust avaliable?

A

Low pressure altitude and low temperature

64
Q

How does a low AR wing compare to a high AR wing?

A

a low AR wing cannot produce as high a CL as a high AR wing (a low AR wing also has a much higher stall speed)

65
Q

How does drag compare on a low AR wing vs. a high AR wing?

A

a low AR wing produces more induced drag at low airspeeds and less parasite drag at high airspeeds (the T-38C)

66
Q

How does wing sweep affect Cl?

A

a swept wing generates less CL than a straighter wing

the longer chord and spanwise flow is a shallower lift curve slope and a lower CL max

67
Q

How does stall angle of attack change with a swept wing?

A

a swept wing is less sensitive to changes in AoA because of its shallower curve slope (you can reach a higher AoA before stall occurs)

however, at slow airspeed a higher AoA is required for the same CL b/c lift production is less efficient with swept wings

68
Q

What is one of the main reasons for sweeping a wing?

A

Reduce parasite drag at higher airspeeds (by decreasing the frontal area but still maintaining the wing surface area)

However, b/c induced drag is inversely proportional to AR, a swept wing generates more induced drag at low airspeeds

69
Q

What kind of wing does the T-38 have?

A

symmetric, low AR, tapered, and swept-back

70
Q

Where does the T-38 wing first stall at?

A

at the wingtips first (unlike a straight cambered wing)

71
Q

A low aspect ratio wing produces ___ parasite drag at high speed as compared to a high aspect ration wing with the same surface area

A

less parasite at high speeds

72
Q

In general, sweeping a wing aft will ____ the CL for a given AoA

73
Q

Unlike a conventional straight cambered wing which generally stalls at the ____ first, the T-38’s sweptback symmetrical wing begins to stall at the ___

A

wing root; wingtip

74
Q

What did the T-38 incorporate to control wave drag?

A

Area Rule
-drag at high speeds is a function of the aircraft’s cross-section area…gradual changes allow air to flow smoothly around the aircraft with the least amount of disturbance

75
Q

What does the T-38 have to overcome the increased load forces on the control surfaces at high-speeds?

A

Irreversible flight controls (meaning the pilot has no direct connection from the flight controls)

76
Q

What kind of all-moveable control surface does the T-38 have to deal with shock-induced separation?

A

Horizontal Stabilator

77
Q

What design features improve the T-38’s high speed flight performance?

A

Area rule, irreversible flight controls, and a large horizontal stabilator

78
Q

What is subsonic, transonic, and supersonic flight?

A

Subsonic: airflow at a speed less than the speed of sound

Transonic: mixed airflow that is part subsonic and part supersonic

Supersonic: airflow at a speed greater than the speed of sound

79
Q

What is the speed of sound? Is it constant?

A

-the rate at which pressure waves propagate through air
-speed of sound is not constant, it depends primarily on temperature

80
Q

What is the key factor which determines the speed of sound?

A

Temperature

81
Q

What is Mach number?

A

used to measure the speed of an aircraft; the ratio of an aircraft’s true airspeed to the speed of sound