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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