Flashcard decks

Module 8 Set 5 AST

31 flashcardsby Adam
Study these flashcardsFree · spaced repetition · iPhone, Android, Mac & web

All cards

1
The lift produced by an aero foil
  • Varies with the area of the aero foil
  • Depends primarily on the thrust that each engine produces
  • Varies directly with the area of the aero foil
2
The coefficient of lift
  • Decreases with an increase in airspeed
  • Increases as the centre of pressure move rearwards
  • Increases with an increase in angle of attack
3
Lift coefficient may be increased by
  • Increasing the wing angle of attack
  • Increasing forward speed
  • Gaining height
4
A typical aero foil at zero degrees angle of attack will produce
  • No lift
  • No drag
  • Some lift and drag
5
The centre of pressure will move, over a cambered aero foil, in a normal working range aft of the leading edge by
  • 5% - 10%
  • 25% - 30%
  • 35% - 45%
6
If the weight of an aircraft is increased, the profile drag at a given speed will
  • Increase
  • Decrease
  • Remains the same
7
Airflows mixing at airframe junctions will normally lead to
  • Interference drag
  • Induced drag
  • Form drag
8
The induced drag of an aircraft is the drag due to the
  • Lift being produced
  • Surface roughness
  • Frontal area
9
One of the benefits of a ‘High Aspect Ratio’ wing is to reduce the
  • “Zero Lift” aircraft drag
  • Parasite drag
  • Induced drag
10
Zero lift drag will only occur when the aircraft is in
  • Steep dive
  • Shallow glide
  • Truly vertical flight
11
At the transition point the boundary layer becomes
  • Thinner with turbulent flow
  • Thicker with laminar flow
  • Thicker with turbulent flow
12
The airflow over an aircraft wing of finite length is considered to be
  • Steady
  • Two dimensional
  • Three dimensional
13
Airflow around a cylindrical body becomes turbulent at the
  • Transition point
  • Stagnation point
  • Terminal velocity
14
The stagnation point on an aero foil is the point where the
  • Suction pressure reaches a maximum
  • Airflow is brought completely to rest
  • Boundary layer changes from laminar to turbulent
15
Downstream from the leading edge of an aero foil, the boundary layer will
  • Thicken
  • Thin out
  • Become laminar
16
The layer of air extending from the surface of an object to the point where no dragging occurs is known as
  • Stagnation layer
  • Turbulent layer
  • Boundary layer
17
The angle of attack of an aero foil is the angle that the
  • Chord line makes with the longitudinal axis
  • Chord line makes with the relative airflow
  • Airframe makes with the horizontal when the aircraft is in a rigging position
18
The chord line of an aero foil is
  • A line, each point of which is equal distant from the upper and lower surfaces of an aero foil section
  • A straight line drawn through the centers of curvature at the leading and trailing edges of an aero foil section
  • A straight line tangential to the top surface at the leading edge
19
Wash out will ensure
  • Tip of the wing stalls first giving a greater warning to the pilot of a complete stall
  • Root of the wing stalls first maintaining control over the ailerons
  • Complete wing stalls at once reducing the risk of structural failure
20
Washout on a wing refers to
  • A greater angle of incidence at the wing root than at the wing tip
  • An increase in angle of incidence from the wing root to the wing tip
  • The distance between the leading and and trailing edge of a wing
21
An aero foil with zero camber will
  • Have a reflex trailing edge
  • Be symmetrical in section
  • Have a concave lower section
22
A common feature designed to prevent wing tip stall is
  • A reduction in incidence at the tips, called washout
  • The use of slats to increase the stalling angle
  • Root spoilers to cause airflow breakaway
23
As the angle of attack increases
  • Induced drag decreases
  • Induced drag increases
  • Wingtip vortices decrease
24
On an aero foil section, as the angle of attack is increased, the
  • Transition point moves towards the trailing edge
  • Stagnation point moves away from the leading edge underneath the wing
  • Stagnation point moves round the leading edge to towards the transition point
25
When the angle of attack of an aero foil is increased
  • The lift coefficient increases as the centre point of pressure moves rearwards
  • A forward movement of the centre of pressure coincides with an increase of the lift coefficient
  • The coefficient of lift reduces with an increase in drag
26
As an airflow approaches an aero foil at an angle of attack it experiences
  • Upwash
  • Downwash
  • A vortex
27
On a rectangular wing platform a small stall strip is installed on the inboard section of the wings leading edge to ensure
  • The outboard section of the wing stalls first
  • Elevator control is not lost at the beginning of a stall condition
  • The wing root area stalls first allowing the aileron control to continue throughout the stall
28
If two identical aeroplane with a large difference in their weight are stalled
  • The heavier will have a higher stalling speed than the lighter
  • The lighter will have a higher stalling speed than the heavier
  • They will both stall at the same speed
29
An aircraft wing is designed to stall
  • Along the whole length simultaneously
  • Progressively from root to tip
  • Progressively from tip to root
30
If the throttle is opened and the angle of attack is held constant, the airspeed and altitude are
  • Increased continuously at a constant rate
  • Increased initially then stabilized at new values
  • Unchanged
31
When viewed from the rear, wingtip vortices rotate
  • Clockwise on the port wing, anti clockwise on the starboard wing
  • Anti clockwise on the port wing, clockwise on the starboard wing
  • Anti clockwise on both wings
Study all 31 cards for free