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Flight School > Performance & Limitations > Flashcards

Performance & Limitations Flashcards

1
Q

4 Dynamic Forces

A

Lift- Upward Acting Force

Gravity (weight)- Downward Acting Force

Thrust- Forward

Drag- Backward

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2
Q

Sum of opposing forces is equal

A

Steady-state, straight and level unaccelerated flight

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3
Q

Airfoil

A

Air moving over surface = lift

Wings, horizontal & vertical tail surfaces, propellers

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4
Q

Angle of Incidence

A

Angle formed by Longitudinal Axis & Chord of wing, fixed and cannot be changed

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5
Q

Relative Wind

A

Direction of airflow with respect to wing

Wing forward & downward- relative wind backward & upward

Flight path and relative wind always parallel but travel in opposite directions

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6
Q

Angle of attack

A

Angle wing chord line & direction of relative wind

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7
Q

Bernoullis Principle

A

Pressure of fluid decreases at points where the speed of fluid increases

High speed flow - low pressure
Low speed - high pressure

Pressure decrease of pressure above wing and increase below produces lift

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8
Q

Factors affecting lift and drag

A
  1. Wings (Pilot can change with flaps)
  2. Airfoil shape (upper curvature of airfoil increased, lift increased- lowering aileron/flap)
  3. Angle of Attack (increased also increased lift and drag)
  4. Air Velocity (air passing over wing increased lift and drag)
  5. Air Density (pressure, temp, and humidity defect density which effects lift & drag- increase, increase, decrease, decrease)
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9
Q

Torque Effect

A

Newton’s third law of physics- every action there is equal and opposite reaction

Internal engine parts + propeller turn one direction = equal force trying to rotate plane other direction

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10
Q

Torque Effect 4 Factors

A
  1. Reaction of Engine & Propeller- propeller to right is making plane roll and bank left
  2. gyroscopic effect of Propeller- if axis of propeller tilted resulting force exerted 90 degrees ahead in direction of rotation
  3. Corkscrewing effect of propeller- high speed rotation results in corkscrewing of slip stream moving rearward. Pushes tail to right and yaws plane to left.
  4. P-factor- high angle of attack downward bite of propeller greater than bite of upward moving blade. Plane yaws left
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11
Q

Centrifugal Force

A

Equal & Opposite reaction of plane changing direction, acting equal and opposite to horizontal component of lift

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12
Q

Load factor

A

Actual load supported by wings divided by total weight of plane

Plane can be overloaded and increases stall speed

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13
Q

Maximum load factor

A

Load factor Max during bank angle after 45-50 degrees

Turbulence could cause increase in angle of attack

Speed- flying below maneuvering plane can stall before load factor excessive, faster can be exceeded by controls or strong turbulence

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14
Q

Maximum Safe (Limit) Load Factors
Normal Airplane

A

+3.8 to -1.52

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15
Q

Maneuvering Speed

A

Max speed at which limit load can be imposed without causing structural damage (by gusts or full deflection of control surfaces)

Maneuvering speed increase with increased weight, decreases decreased

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16
Q

LOC-I

A

Loss of control inflight
Significant deviation of aircraft from intended path

LOC-I accidents occur from uncoordinated flight, equipment malfunctions, pilot complacency, distraction, poor risk management

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17
Q

Stall causation

A

Increased angle of attack, airflow separated from upper surface of wing

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18
Q

Spin

A

Descent in helical path which flying aoa greater than critical aoa. Aggravated stall in slip or skid.

19
Q

Scenarios spin likely

A

Engine failure on take off (increased back pressure/uncoordinated turn)

Slipping or skidding turn from base to final (uncoordinated turn at low speed)

Engine failure on approach to landing (increased back pressure to stretch glide)

Go around with full nose up trim

Go around with improper flap retraction (retracts flaps rapidly causing rapid sink rate and instinctual back pressure)

20
Q

Spin Recovery

A

PARE
Power Idle
Ailerons Neutral
Rudder Opposite
Elevator FWD

Then neutralize rudder & begin applying back pressure to return to level

21
Q

Adverse Yaw

A

Turning left-
Down aileron on right producing more lift & drag while left aileron has less lift & drag.
This added drag attempts to pull airplanes nose in direction of raised wing. (Adverse yaw)

22
Q

Ground effect

A

Airflow around wing restricted by ground surface reducing wings upwash, downwash, and wingtip vortices

Reduced drag on landing and take off:

Excess speed during landing = significant float

Deficiency of speed during take off = marginal climb performance of inability to fly

23
Q

Empty Weight

A

Weight of airframe, engines, all permanently installed aircraft, unusable fuel

24
Q

Gross Weight

A

Maximum allowable weight (airplane + contents)

25
Q

Useful Load

A

Weight of Pilot, copilot, passengers, baggage, usable fuel, drain able oil

26
Q

Arm

A

Horizontal distance in inches from reference datum line to center of gravity of item

27
Q

Moment

A

Weight of an item multiplied by its arm, expressed in pounds-inches

28
Q

Center of gravity

A

Point at which aircraft would balance if it were possible to suspend it at that point

Inches from datum

29
Q

Datum

A

Imaginary vertical plane or line from which measurements of arm are taken, established by manufacturer

30
Q

Center of Gravity Equations

A

Weight x Arm = Moment
Moment/Arm = Weight
Total Moment / Total Weight = Arm (CG)

31
Q

Weight Shift

A

Shifting weight around aircraft, weight remains same BUT total moment change in relation and proportion to direction and distance the weight moved

Weight forward, moment decreased
Weight aft, moment increases

32
Q

Weight Shift Equation

A

Weight Shifted divided by total weight
Equals
Change in CG divided by distance weight is shifted

33
Q

FWD Center of gravity

A

Higher Stall Speed -increased wing loading

Slower cruise speed- increased drag, greater aoa to maintain altitude

More stable- farther fwd from center of pressure, increases longitudinal stability

Greater back elevator pressure required- longer take off roll, higher approach speeds & problems with landing flare

34
Q

Rearward center of gravity

A

Lower stall speed- less wing loading

Higher cruise speed- reduced drag, smaller aoa required to maintain alt

Less stable- stall & spin recovery more difficult, COG closer to COP

35
Q

Standard weights

A

Crew & pax 190 each
Av gas 6 lb/gal
Jet A 6.75 lb/gal
Oil 7.5 lb/gal
Water 8.35 lb/gal

36
Q

New avionics installed, weight and balance record required?

A

A& P mechanic or tech’s responsibility to know weight and location of changes and to compute the CG and record new empty weight and empty weight center of gravity EQCG in aircraft weight and balance record

37
Q

Wind & Aircraft Performance

A

Takeoff- headwind allows ac to reach lift off speed at lower ground speed, shortening take off distance and increasing aoa

Landing- headwind lowers ground speed and steepens approach angle, reducing landing distance

Cruise- headwind decreases performance by reducing ground speeds, tailwind increases

38
Q

TO/Landing Performance - Weight

A

Take off- increased weight:
Higher liftoff speed
Slow acceleration
Increased drag & ground friction
Longer take off distance

Landing:
Increased landing distance

39
Q

TO/Landing Performance- Density Altitude

A

Increased:
TO Distance (greater TAS required)
True airspeed on approach and landing
Landing roll distance

Reduced rate of climb

40
Q

Density Altitude

A

Pressure altitude corrected for nonstandard temperature

Vertical distance above sea level in the standard atmosphere at which a given density is found

41
Q

Aircraft performance - Air Density

A

Density effects-
Lift produced by wings
Power output of engine
Propeller efficiency
Drag forces

42
Q

Factors affecting air density

A

Altitude (higher, less dense, density altitude increases)
Temp (warmer, less dense)
Humidity (more humid, less)

43
Q

Best glide speed vs min sink rate

A

Best glide is greatest distance for loss of altitude

Best sink maximizes time remains in flight, lowest rate for losing altitude

44
Q

Pressure Altitude

A

Altitude indicated when altimeter adjusted to 29.92 altitude above standard datum plane

Flight School (16 decks)

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