Module 8 Set 2 AST

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1
The troposphere is a layer of the atmosphere where the temperature
  • Generally decreases with height
  • Generally increases with height
  • Remains constant
2
Pressure changes with change in volume (at constant temperature) so that it doubles when the volume
  • Doubles
  • Halves
  • Quadruples (x4)
3
Millibars are units of
  • Pressure
  • Density
  • Force
4
Density of the atmosphere will
  • Increase with rising humidity
  • Decrease with rising humidity
  • Be unaffected by any change in humidity
5
The standard sea level pressure in the ISA is normally measured in millibars. Its metric equivalent in kilo-Pascal's is
  • 1013.00
  • 1003.20
  • 101.325
6
Mach number is the ratio of the aircraft's
  • True air speed to the speed of sound at sea level
  • True air speed to the speed of sound at the same atmospheric conditions
  • Indicated air speed to the speed of sound at the same atmospheric conditions
7
The angle of attack of an aero foil is the angle that the chord line makes with the
  • Longitudinal axis
  • Direction of motion
  • Horizontal when the aircraft is in a rigging position
8
If the airspeed over a wing at a constant angle of attack is doubled, the lift will be
  • Doubled
  • Quadrupled (x4)
  • Increased by a power of eight
9
Aspect ratio is the ratio of aero foil
  • Mean chord to span
  • Span to mean chord
  • Thickness to mean chord
10
The optimum angle of an aero foil is that angle at which the
  • Aero foil produces maximum lift
  • Aero foil experiences minimum drag
  • Best lift/drag ratio is produced
11
If the throttle is opened and the airspeed is held constant, the angle of attack is
  • Increased
  • Decreased
  • Unchanged
12
The transition point on a wing is the point where the
  • Flow separates from the wing surface
  • Boundary layer flow changes from laminar to turbulent
  • Flow divides to pass above and below the wing
13
If an aircraft is flying at constant speed then thrust is
  • Greater than drag
  • Equal to drag
  • Less than drag
14
The weight of an aircraft is considered to act at the center of
  • Pressure
  • Gravity
  • Lift
15
During a turn the lift force is resolved into two forces which are centripetal and a force equal and opposite to
  • Drag
  • Weight
  • Thrust
16
A high L/D ratio
  • Gives a steep glide angle
  • Has no effect on the glide angle
  • Gives a shallow glide angle
17
In a climb, the lift force is
  • Less than the weight
  • Equal to the weight
  • Greater than the weight
18
During a glide the forces acting on an aircraft are
  • Lift, weight and thrust
  • Lift, drag and weight
  • Drag, thrust and weight
19
Stability about the lateral axis is given by the
  • Wing dihedral
  • Horizontal stabilizer
  • Ailerons
20
Anhedral of a wing will
  • Aero foil produces maximum lift
  • Reduce longitudinal stability
  • Reduce lateral stability
21
Pitch up in an aircraft is caused by
  • Longitudinal instability
  • Lateral instability
  • Air compressibility
22
Dutch roll is
  • A combination of rolling and yawing motions
  • A type of very slow rolling motion
  • Primarily a pitching instability
23
Increasing the size of the vertical stabilizer will
  • Increase lateral stability
  • Decrease lateral stability
  • Have no effect on lateral stability
24
Moving the C of G aft will
  • Reduce longitudinal stability
  • Increase longitudinal stability
  • Decrease lateral stability
25
Washout on a wing is when the incidence
  • Decreases from root to tip
  • Decreases from tip to root
  • Increases from root to tip
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