## What does every number of NACA 4412 airfoil mean?

The NACA 4412 is a four digit airfoil. The first digit expresses the camber in percent chord, the second digit gives the location of the maximum camber point in tenths of chord, and the last two digits gives the thickness in percent chord.

**Where is NACA 4412 used?**

sports plane

The NACA 4412 has been used in sports plane. The example includes AAI-AA2 mamba aircraft, aeronca series aircraft like aeronca 65-tac defender, aeronca 11ac chief etc while the S1223 is an airfoil used in heavy lift cargo planes [2].

**Where is NACA 0012 used?**

NACA 0012 airfoil is chosen to model and simulate processes of computational fluid dynamics. Analyzes to obtain velocity and pressure distribution on the wing surface were performed using ANSYS Fluent software. Also, the drag and lift coefficients were calculated according to variable relative velocities.

### What is the difference between a 4 and 5 digit NACA number?

The NACA Five-Digit Series uses the same thickness forms as the Four-Digit Series but the mean camber line is defined differently and the naming convention is a bit more complex. The first digit, when multiplied by 3/2, yields the design lift coefficient (cl) in tenths.

**How do you read NACA 5 Series?**

NACA Five-Digit Series: The first digit, when multiplied by 3/2, yields the design lift coefficient (cl) in tenths. The next two digits, when divided by 2, give the position of the maximum camber (p) in tenths of chord. The final two digits again indicate the maximum thickness (t) in percentage of chord.

**What can we learn from NACA 4412 experiments?**

Methodology This series of NACA 4412 experiments was conducted in Cal Poly’s open-loop low speed wind tunnel in a variety of testing conditions. The force balance experiment offered useful information on how the force and moment coefficients vary with Reynolds Number and aspect ratio.

## What is the NACA 4412 code?

NACA 4412 Airfoil 4 digit code used to describe airfoil shapes 1st digit – maximum camber in percent chord 2nd digit – location of maximum camber along chord line (from leading edge) in tenths of chord 3rd and 4th digits – maximum thickness in percent chord NACA 4412 with a chord of 6” Max camber: 0.24” (4% x 6”)

**Is the NACA 4412 a successful airfoil?**

These results agree with experimental data found in literature and suggest that the tests performed on the NACA 4412 airfoil were successful. V. Appendices A. Raw v Processed Data Table 6.

**Can a NACA 4412 be towed at a Reynolds number of 8×10?**

Kikuchi et al. (2002) present results obtained on a NACA 4412 airfoil towed at a Reynolds number of 8×10 5. Although the flow is still below the general WIG operating range, practical aerodynamic trends are obtained.