Understanding the NACA 64(1)2-212a Airfoil
Understanding the NACA 64(1)2-212a Airfoil
NACA 6-Series Airfoil Explorer
Understanding the NACA 64(1)2-212a Airfoil
Introduction to NACA 6-Series Airfoils
The NACA 6-series airfoils were developed by the National Advisory Committee for Aeronautics (NACA) to provide laminar flow over a large portion of the chord. This results in lower drag compared to earlier airfoil designs.
NACA 64(1)2-212a Breakdown
| Component | Meaning | Value |
|---|---|---|
| 6 | Series designation | 6-series airfoil |
| 4 | Location of minimum pressure | 0.4c (40% of chord) |
| (1) | Range of lift coefficients | ±0.1 around design lift coefficient |
| 2 | Design lift coefficient | 0.2 |
| 12 | Maximum thickness | 12% of chord |
| a | Laminar flow maintenance | Special designation (defaults to 1.0 if not specified) |
Lift Coefficient vs. Angle of Attack
This chart shows how the lift coefficient (CL) changes with angle of attack for different Reynolds numbers.
About Lift Coefficients
The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by an airfoil to the fluid density, fluid velocity, and the reference area.
For the NACA 64(1)2-212a, the design lift coefficient is 0.2, with a range of ±0.1 around this value.
Drag Polar
This chart shows the relationship between lift coefficient (CL) and drag coefficient (CD) for different Reynolds numbers.
About Drag Polars
The drag polar shows the relationship between lift and drag, which is crucial for understanding an airfoil's efficiency. The point closest to the origin represents the most efficient operating condition.
Technical Details
Mathematical Formulation
The NACA 6-series airfoils are defined using complex mathematical equations that describe the mean camber line and thickness distribution.
yc = (c/2π) * [ (1 - x/c) * ln(1 - x/c) + (x/c) * ln(x/c) ]
yt = 5t * [0.2969√(x/c) - 0.1260(x/c) - 0.3516(x/c)2 + 0.2843(x/c)3 - 0.1015(x/c)4]
Laminar Flow Characteristics
The "a" designation in NACA 64(1)2-212a indicates special laminar flow maintenance properties. This airfoil is designed to maintain laminar flow over a significant portion of the chord, reducing skin friction drag.
Applications
NACA 6-series airfoils are commonly used in:
- General aviation aircraft
- Gliders and sailplanes
- Wind turbine blades
- Propellers