Lift & Drag Calculator
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Calculate lift and drag forces for an aircraft based on flight conditions, wing geometry, and airfoil characteristics. This calculator uses simplified aerodynamic models suitable for preliminary design.
Flight Conditions
Angle in degrees
Wing Geometry
Airfoil Characteristics
Lift & Drag Results
Lift Force
17,139.33 N
CL = 0.771
Drag Force
1,370.37 N
CD = 0.0616
Performance Metrics
Lift/Drag Ratio
12.5
Max L/D = 21.1
Stall Speed
8.96 m/s
32.26 km/h
Optimal AOA
0.3°
For max L/D ratio
Aspect Ratio
4.0
Span²/Area
Flight Conditions
Velocity
50.00 m/s
180.00 km/h ≈ 97.19 knots
Altitude
1,000.00 m
3,280.84 ft
Air Density
1.1117 kg/m³
Dynamic pressure: 1,389.56 Pa
Airfoil
NACA 2412
CLmax: 1.40 | CD0: 0.0060
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
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