C06 - Introduction to Lift Flashcards
What is the Lift Equation?
L = Clmax x ½ pV² x A.
Define Lift Coefficient?
The amount of lift produced per unit area and unit dynamic pressure.
What three main factors affect the lift coefficient on the aerofoil?
- Angle of Attack.
- Thickness.
- Camber.
Up to a certain angle (stalling/critical), an increase in ‘____’ causes the airflow over the upper surface to travel ‘____’. This reduces the ‘____’ over the upper surface (3)?
- Angle of Attack.
- Faster.
- Pressure.
For a symmetrical aerofoil, if the Angle of Attack doubles, what happens to the coefficient of lift?
It also doubles.
What does Clmax stand for?
Maximum value of the coefficient of lift.
What is the Stalling Angle?
16°.
Define the Thickness-Chord ratio?
The ratio of the aerofoil’s maximum thickness to the length of its chord.
Name three factors which are associated with coefficient of lift when the thickness of a symmetrical aerofoil increases?
- Clmax Increases.
- Stalling Angle Increases.
- The rate of Clmax increases with Angle of Attack are approximately the same.
Name three effects of deploying the Trailing Edge Flaps during low-speed flight?
- Increases Camber of the Wing.
- Increases the Clmax.
- Reduces the Stalling Angle.
If the wing area and coefficient of lift is doubled, what happens to lift?
Will double.
If IAS is doubled, what will happen to lift?
Four times greater.
Whilst accelerating to cruise speed in flight, the pilot must ‘____’ to reduce the ‘____’ in order to keep lift constant (2)?
- Progressively lower the nose of the Aircraft.
- Angle of Attack.
As IAS is reduced the coefficient of lift must be ‘____’ to keep the lift constant? The pilot must ‘____’ in order to increase the Angle of Attack (2)?
- Increased.
- Progressively raise the nose of the Aircraft.
