Understand, visualize, and analyze NACA 4-digit airfoils
Understand, visualize, and analyze NACA 4-digit airfoils
NACA 4-Series Airfoil Explorer
Understand, visualize, and analyze NACA 4-digit airfoils
What are NACA 4-Series Airfoils?
The NACA 4-digit airfoil series is a set of standardized airfoil shapes developed by the National Advisory Committee for Aeronautics (NACA), the predecessor to NASA. The 4-digit code defines the airfoil's geometric characteristics:
Example: NACA 2412
First digit (2): Maximum camber as a percentage of the chord (2%)
Second digit (4): Position of maximum camber in tenths of chord (40% or 0.4c from leading edge)
Last two digits (12): Maximum thickness as a percentage of chord (12%)
These airfoils were widely used in early aviation and are still studied for their fundamental aerodynamic properties.
Airfoil Generator
Airfoil Parameters
| Parameter | Value |
|---|---|
| Maximum Camber | 2% |
| Position of Maximum Camber | 40% |
| Maximum Thickness | 12% |
| Chord Length | 1.0 m |
Aerodynamic Performance
Performance at 0° Angle of Attack
| Parameter | Value |
|---|---|
| Lift Coefficient (CL) | 0.25 |
| Drag Coefficient (CD) | 0.015 |
| Moment Coefficient (CM) | -0.05 |
NACA 4-Series Airfoil Explorer
Understand, visualize, and analyze NACA 4-digit airfoils
What are NACA 4-Series Airfoils?
The NACA 4-digit airfoil series is a set of standardized airfoil shapes developed by the National Advisory Committee for Aeronautics (NACA), the predecessor to NASA. The 4-digit code defines the airfoil's geometric characteristics:
Example: NACA 2412
First digit (2): Maximum camber as a percentage of the chord (2%)
Second digit (4): Position of maximum camber in tenths of chord (40% or 0.4c from leading edge)
Last two digits (12): Maximum thickness as a percentage of chord (12%)
These airfoils were widely used in early aviation and are still studied for their fundamental aerodynamic properties.
Airfoil Generator
Airfoil Parameters
| Parameter | Value |
|---|---|
| Maximum Camber | 2% |
| Position of Maximum Camber | 40% |
| Maximum Thickness | 12% |
| Chord Length | 1.0 m |
Aerodynamic Performance
Performance at 0° Angle of Attack
| Parameter | Value |
|---|---|
| Lift Coefficient (CL) | 0.25 |
| Drag Coefficient (CD) | 0.015 |
| Moment Coefficient (CM) | -0.05 |