Understand, visualize, and analyze NACA 5-digit airfoils
Understand, visualize, and analyze NACA 5-digit airfoils
NACA 5-Series Airfoil Explorer
Understand, visualize, and analyze NACA 5-digit airfoils
What are NACA 5-Series Airfoils?
The NACA 5-digit airfoil series is a more advanced set of airfoil shapes developed by the National Advisory Committee for Aeronautics (NACA). The 5-digit code defines more sophisticated airfoil characteristics:
Example: NACA 23012
First digit (2): Design lift coefficient (2 × 3/2 = 3, or 0.3)
Second digit (3): Position of maximum camber (3 × 5 = 15% of chord)
Third digit (0): Type of camber line (0 = standard camber)
Last two digits (12): Maximum thickness as percentage of chord (12%)
These airfoils were designed for more specific performance characteristics than the 4-digit series.
Airfoil Generator
First digit: Design lift coefficient (cl = L × 3/20)
Second digit: Max camber position (P × 5% of chord)
Third digit: 0 = standard, 1 = reflexed camber
Last two digits: Maximum thickness (% of chord)
Airfoil Parameters
| Parameter | Value |
|---|---|
| Design Lift Coefficient | 0.3 |
| Position of Maximum Camber | 15% |
| Camber Type | Standard |
| Maximum Thickness | 12% |
Aerodynamic Performance
Lift Coefficient
Drag Coefficient
Moment Coefficient
Performance at Design Condition
| Parameter | Value |
|---|---|
| Lift Coefficient (CL) | 0.30 |
| Drag Coefficient (CD) | 0.012 |
| Moment Coefficient (CM) | -0.04 |