Airfoil Lift Lab

Introduction to Flight · Airfoils and lift production

Pilot

Pilot can change
0%
0°
0 kt
0°

Throttle sets airspeed. Pitch sets angle of attack.

The air moves past a wing held still.

Flaps

Pilot changes camber

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Aircraft design

Set by the designer
0%
0%
0 ft²
0 lb

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Atmosphere

No pilot control
0 ft

Air density 100% of sea level. Higher up, fewer air molecules reach the wing.

Airspeed
0KT
Altitude
0FT
Vertical speed
0FPM
Pitch
0°
Angle of attack
0°
Flight path
0°
Lift
0LB
Drag
0LB
Thrust
0LB
Weight
0LB
Lift ÷ weight
0×
Critical angle
0°
Side view · four forces
Level Pitch 0° = angle of attack 0° + flight path 0° The moving air makes the relative wind.
Wing cross-section · airflow
Slower air, higher pressureFaster air, lower pressure Bright bands left the rake together

The five lift factors

Lift =½ ×ρ×V²×S×CL

Angle of attack0°Pilot · pitch
Airspeed (V)0 ktPilot · throttle
Camber0%Pilot · flaps only
Wing area (S)0 ft²Designer
Air density (ρ)0% of sea levelNo control

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CL, the lift coefficient, combines angle of attack and camber. Lift grows with the square of airspeed: twice the speed gives four times the lift.

Lift curve

Lift coefficient CL Drag coefficient CD

Try it

Do this

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Notice

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Simplified classroom model, close to a four-seat trainer (174 ft² wing, 2,300 lb). In the side view, thrust and drag arrows are drawn four times longer than lift and weight so they stay visible. Angle of attack is measured from the chord line with flaps up. Hover a control for a short tip.