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WorksheetsCPL PoF Lift Revision 1
Total questions: 20
Worksheet time: 10mins
The upward movement of air at the LEADING edge is known as:
The total reaction
Upwash
Downwash
Leftwash
The point at the leading edge where air comes to a complete stop is know as:
The stop point
The stationary point
The stagnation point
The zero speed point
For a general purpose aerofoil the AoA for zero lift is:
4° AoA
0° AoA
-4° AoA
-6° AoA
At the zero lift angle:
No lift is produced
A small amount of lift is produced
The aircraft will stall
No net lift is produced
For a general purpose aerofoil what is the critical angle and what happens if it is exceeded
16° the aircraft will stall
18° the aircraft will fly backwards
16° the amount of life will continue to increase
18° the aircraft will stall
Which of the these pressure envelopes represents an aerofoil at the critical angle (16°)
A
B
C
D
How does downwash effect the generation of lift:
Downwash increases lift by increasing the effective AoA
Downwash decreases lift by increasing the effective AoA
Downwash increases lift by decreasing the effective AoA
Downwash decreases lift by decreasing the effective AoA
Centre of Pressure:
Is the point where weight acts through
Is the point where upwash acts through
Is the point downwash acts through
Is the point lift acts through
The approximate movement of the centre of pressure as a % of the chord is:
40% of chord at low AoA to 15% at high AoA
15% at low AoA to 40% at high AoA
Stays at approximately 40% at both low and high AoA
Stays at 15% chord regardless of AoA
What happens to the total reaction with an increase in AoA
Decreases and tilts forwards
Increases and tilts forwards
Decreases and tilts backwards
Increases and tilts backwards
Tick all attributes of an ideal aerofoil
High Max CL
Low Minimum Cd
Low Lift/Drag ratio
Large and stable movement of CoP
Sufficient Depth
What will having a high maximum CL do to an aircraft's landing speed/landing distance
It will increase landing speed and increase landing distance
It will decrease landing speed and decrease landing distance
It will decrease landing speed and increase landing distance
It will increase landing speed and decrease landing distance
What is a benefit of having sufficient depth? Check all that apply
An aircraft will cruise faster
Allows for more fuel tanks
Greater spar strength for the same weight
Aircraft will be able to glide a greater distance
Lift is:
The component of the total reaction acting inline with the RAF
The component of drag caused by friciton
The component of the total reaction acting inline with the RAF in the direction of motion
The component of the total reaction acting 90° to the RAF through the CoP
The lift formula is?
CL ½pV² CD
CD ½pVs
CL ½pVs²
CL ½pV²s
Coefficient of lift is dependent on? (Tick all that apply)
Angle of Attack
Shape of the wing
True airspeed
Condition of the wing surface
A general purpose aerofoil will still generate lift at 0° AoA
True
False
Camber is a measure of:
The length of an aerofoil
The curvature of an aerofoil
The weight of an aerofoil
The amount of lift produced by an aerofoil
Increasing camber will:
(Tick all that apply)
Increase lift
Increase drag
Decrease lift
Decrease drag
This picture is showing the effect of
Wingtip vortices
Wing root vortices
Propeller slipstream
Ground effect
