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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