What NACA 2412?

NACA 2412 is the airfoil of NACA 4 digit series. From its designation we get 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. Four-digit series airfoils by default.

What is CL Max for NACA 2412?

NACA 2412 airfoil at a Reynolds number of 230,000 (scaled model) is 1.35, whereas the Cl,max of the NACA 2412 airfoil at a Reynolds number of 2,700,000 (full-scale aircraft) is 1.75.

How is NACA airfoil determined?

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

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

What is the thickness in NACA 2412 airfoil?

12%
With all percentages given in respect to the length of the chord, the classification of the NACA 2412 determines that the airfoil has a maximum camber of 2% located at 40% from the leading edge, with a maximum thickness of 12%. The professor desired to experiment with the learning process of the honors students.

Is NACA 2412 symmetrical?

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. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber.

What is maximum camber?

Maximum camber is the maximum distance of the mean camber line from the chord line; Maximum thickness is the maximum distance of the lower surface from the upper surface.

What is aerofoil used for?

Airfoil, also spelled Aerofoil, shaped surface, such as an airplane wing, tail, or propeller blade, that produces lift and drag when moved through the air. An airfoil produces a lifting force that acts at right angles to the airstream and a dragging force that acts in the same direction as the airstream.

What is aerofoil span?

Wing span is the distance from one wing tip to the other wing tip. The ratio of wing length to chord is called the aspect ratio. The amount of lift and drag generated by an aerofoil depends on its shape (camber), surface area, angle of attack, air density and speed through the air.

How is the camber of a NACA airfoil determined?

This NACA airfoil series is controlled by 4 digits e.g. NACA 2412, which designate the camber, position of the maximum camber and thickness. If an airfoil number is M is the maximum camber divided by 100. In the example M=2 so the camber is 0.02 or 2% of the chord

What are the parts of the NACA 2412 airfoil?

The NACA 2412 airfoil was designed and printed as three separate parts. The central part is mostly hollow, containing two slots which a metal bar acting as a spar runs through to connect the three parts. On the surface of the central part, there are 36 small holes that are distributed strategically across the top and bottom of the airfoil.

How to calculate the final airfoil envelope in NACA?

The equation for the camber line is split into sections either side of the point of maximum camber position (P). In order to calculate the position of the final airfoil envelope later the gradient of the camber line is also required. The equations are: The constants a0 to a4 are for a 20% thick airfoil.

How is the airfoil of a NACA generator created?

The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber line. The equation for the camber line is split into sections either side of the point of maximum camber position (P).