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Module 8 Set 3 AST

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1
The airflow pattern around an aircraft at low speed depends mainly on the
  • Shape of the aircraft and its attitude relative to the free stream airflow
  • Attitude of the aircraft and the speed of the relative airflow
  • Shape of the aircraft and the speed of the relative airflow
2
When an aircraft enters a rolling motion
  • Both wings will generate the same amount of lift
  • The down-going wing will generate more lift
  • The up-going wing will generate more lift
3
An increase in the angle of attack on a symmetrical aero foil would cause the center of pressure to 
  • Move slightly but stay roughly in the center of the aero foil
  • Move forward towards the leading edge
  • Move rearwards towards the trailing edge
4
For an aircraft that has a positive angle of attack, the static pressure below the wing will normally be
  • Greater than the ambient pressure
  • Slightly lower than that of ambient pressure
  • The same as ambient pressure
5
The equation of continuity simply states that
  • Mass can only be changed to another form
  • Mass cannot be created but can be destroyed
  • Air mass flow is a constant
6
Movement about the transverse axis effects 
  • Longitudinal stability
  • Lateral stability
  • Directional stability
7
Dynamic pressure is given by
  • 1/2mp
  • Q
  • 1/2mv^2
8
The pressure co-efficient at the leading-edge stagnation point is
  • +/-1
  • -1
  • +1
9
Stagnation pressure is given by
  • Total head pressure minus static pressure
  • Static pressure plus dynamic pressure
  • Dynamic pressure plus pitot pressure
10
If the critical velocity of a flow becoming turbulent in a pipe of 1 inch is 20 fps, then the critical velocity in a 2 inch pipe would be
  • 5 fps
  • 10 fps
  • 20 fps
11
Viscosity of a gas is affected by changes in
  • Density
  • Pressure
  • Temperature
12
The Reynolds number of a fluid flow, can be stated more easily as the measure of the ratio between the viscous forces and the
  • Inertial forces of the fluid
  • Size and velocity of the fluid
  • Density and velocity of the fluid
13
The greatest contribution to the lift of an aero foil comes from the
  • Upper surfaces of the wing
  • Lower surfaces of the wing
  • Length of wings chord line
14
Static pressure on a asymmetrical aero foil would be greatest at the
  • Leading edge of the wing
  • Stagnation point of the wing
  • Wings center of pressure
15
The static margin of an aircraft is between the
  • Forward center of gravity and the aft center of gravity
  • Aft center of gravity and the neutral point
  • Forward center of gravity and the neutral point
16
On a cambered aero foil, the movement range of the center of pressure normally occurs between
  • 25% - 30% of the chord aft of the leading edge
  • 20% - 30% of the chord away from the trailing edge
  • 40% - 50% of the chord aft of the leading edge
17
On a asymmetrical wing a positive angle of attack in the normal operating range will cause the center of pressure to
  • Increase and move towards the leading edge
  • Increase and move towards the trailing edge
  • Decrease rapidly and move towards the trailing edge
18
On a lift curve the greatest part of the curve would be 
  • Exponential
  • Linear
  • Curved
19
To prevent stall on a vertical stabilizer the
  • Aspect ratio of the stabilizer is increased
  • Aircraft can be fitted with multiple fins of high aspect ratio
  • Sweep back of the stabilizer is increased
20
To increase the directional stability of an aircraft, the center of gravity is
  • Positioned at the neutral point
  • Moved forwards away from the neutral point
  • Moved rearwards away from the neutral point
21
The angle of attack where no lift is generated on a typical asymmetrical is
  • +4
  • 0
  • -4
22
Leading edge vortex flow is normally found on 
  • Regular planforms at high angle of incidences
  • Swept and delta shaped planforms, particularly at low angles of incidences
  • Swept and delta shaped planforms, particularly at high angles of incidences
23
On a 1/10 scale model, the mass is
  • 1/10th of a real aircraft
  • 1/100th of a real aircraft
  • 1/1000th of a real aircraft
24
Tail volume is given by the product of tail area time the 
  • Thickness of the tail
  • Aspect ratio of the tail
  • Moment arm away from center of gravity
25
Downwash from the mainplane has the effect of
  • Increasing the angle of attack of the tailplane
  • Decreasing the effective angle of attack on the tailplane
  • Increasing the lift on the tailplane
26
In subsonic airflow air, is considered to be incompressible up to approximately
  • 300mph
  • 350mph
  • 300kph
27
Aircraft that employ stick-free capability will have 
  • Increased longitudinal stability
  • Decreased longitudinal stability
  • Neutral stability
28
An aircraft that is designed with a large tail area allows for the center of gravity to be moved
  • Beyond the static margin
  • Further aft of the neutral point
  • Further forward away from the neutral point
29
Reynolds number effecting airflow properties depends upon
  • Size, Density, Viscosity and speed
  • Viscosity, Size, Density and speed squared
  • Density, Size, Viscosity and speed squared
30
Increasing the wing dihedral of an aircraft will
  • Increase lateral stability
  • Decrease the lateral stability
  • Increase the aircrafts roll ability
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