Lift & Drag

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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

Velocity

Unit

Altitude

Unit

Angle of Attack

Angle in degrees

Wing Geometry

Wing Area

Unit

Wing Span

Unit

Airfoil Characteristics

Airfoil Type

Lift force

17,139.33 N

CL = 0.771

Drag force

1,370.37 N

CD = 0.0616

Performance

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

Force balance

Lift vector

17,139 N

Drag vector

1,370 N

Angle (α)

5.0°

Free-stream

reference line

Coefficient curve

Lift coefficient (CL)

Drag coefficient (CD)

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Lift & Drag

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Flight Conditions

Velocity

Unit

Altitude

Unit

Angle of Attack

Angle in degrees

Wing Geometry

Wing Area

Unit

Wing Span

Unit

Airfoil Characteristics

Airfoil Type

Lift force

17,139.33 N

CL = 0.771

Drag force

1,370.37 N

CD = 0.0616

Performance

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

Force balance

Lift vector

17,139 N

Drag vector

1,370 N

Angle (α)

5.0°

Free-stream

reference line

Coefficient curve

Lift coefficient (CL)

Drag coefficient (CD)

Open Source and Easy to Use Elsewhere

Open source: review the implementation and see how the results are produced.

Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.

View source code Get embed code

Lift & Drag

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Flight Conditions

Velocity

Unit

Altitude

Unit

Angle of Attack

Angle in degrees

Wing Geometry

Wing Area

Unit

Wing Span

Unit

Airfoil Characteristics

Airfoil Type

Lift force

17,139.33 N

CL = 0.771

Drag force

1,370.37 N

CD = 0.0616

Performance

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

Force balance

Lift vector

17,139 N

Drag vector

1,370 N

Angle (α)

5.0°

Free-stream

reference line

Coefficient curve

Lift coefficient (CL)

Drag coefficient (CD)

Open Source and Easy to Use Elsewhere

Open source: review the implementation and see how the results are produced.

Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.

View source code Get embed code