22.8 Lift

22.8.2 Identify the factors affecting lift (low-subsonic speed airflow).

Wing Shape - Aerofoil Section

Camber

• more camber = more lift 

 Angle of Attack

Angle of Attack (AoA), 

• AoA increases = lift increases

Air Density

p (rho) = Density of air

• ambient density of the free stream air (air not disturbed by the passage of the aircraft)
• higher density = more lift 

True Airspeed V²

V² = Velocity of air (TAS)

• V is the speed the aircraft moves through the air (TAS)
• the force (lift) produced is directly proportional to the airspeed squared
• Velocity increases = lift increases

Wing Surface Area

S = Surface area of the aerofoil (Plan view)

• The size of wing area is directly proportional to the force (lift) produced
• larger wing area = more lift

22.8.4 State the lift formula, and the three basic functions contained within it.

The lift generated by an aerofoil can be calculated using the following formula:

Lift = C_L ½ p V² S 

Where:

• C_L = Coefficient of lift
• p (rho) = Density of air
• V² = Velocity of air (TAS)
• S = Surface area of the aerofoil (Plan view)