Table of Contents

## What does NACA 2415 mean?

NACA 2415 airfoil has a maximum thickness of 15% with a camber of 2% located 40% back from. the airfoil leading edge (or 0.4c). Utilizing these m, p, and t values, we can compute the coordinates. for an entire airfoil using the following relationships: 1.

## How do you read NACA airfoil data?

How do you read NACA airfoil data?

- First digit describing maximum camber as percentage of the chord.
- Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
- Last two digits describing maximum thickness of the airfoil as percent of the chord.

**How is NACA airfoil calculated?**

Equation for a symmetrical 4-digit NACA airfoil

- c is the chord length,
- x is the position along the chord from 0 to c,
- is the half thickness at a given value of x (centerline to surface), and.
- t is the maximum thickness as a fraction of the chord (so 100 t gives the last two digits in the NACA 4-digit denomination).

**How many NACA airfoils are there?**

78 airfoils

By 1929, Langley had developed this system to the point where the numbering system was complemented by an airfoil cross-section, and the complete catalog of 78 airfoils appeared in the NACA’s annual report for 1933.

### What is NACA series?

The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word “NACA”.

### Where is the max camber located for the NACA 2415 airfoil?

At the location of the maximum camber: 40% of the chord (2415-4). Before the transition point (at 0 AOA): 50% of the chord (2415-5).

**What does NACA and NASA stand for?**

The National Advisory Committee for Aeronautics (NACA) came into being, much like its successor organization, the National Aeronautics and Space Administration (NASA), in response to the success of others.

**How do I read a NACA number?**

The NACA four-digit wing sections define the profile by:

- First digit describing maximum camber as percentage of the chord.
- Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
- Last two digits describing maximum thickness of the airfoil as percent of the chord.

#### What NACA 2412?

Two digits describing maximum thickness of the airfoil as percent of the chord. For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.

#### What is the NACA number?

(425) 602-6222 x4.

**What does NACA 0012 mean?**

NACA 0012 mean that there is no camber i.e. zero camber is present, and it has the maximum thickness of the airfoil at 12% of the chord from the leading edge.