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].

What is the maximum thickness of a 60 inch chord wing using a NACA 4415 airfoil?

NACA 4415 – NACA 4415 airfoil Max thickness 15% at 30.9% chord.

What is NACA 6 Series?

A value of 6 indicates that the nose radius is the same as the original airfoil while a value of 0 indicates a sharp leading edge. Increasing this value specifies an increasingly more rounded nose. The second digit determines the location of maximum thickness in tenths of chord.

What is the thickness in NACA 747A315 airfoil?

NACA 747A315 – NACA 747A315 airfoil Max thickness 15% at 40.2% chord.

What makes a good airfoil?

The most efficient airfoil for producing the greatest lift is one that has a concave or “scooped out” lower surface. As a fixed design, this type of airfoil sacrifices too much speed while producing lift and is not suitable for high-speed flight.

What are the NACA airfoil numbers?

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 P is the position of the maximum camber divided by 10.

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”)

How to calculate the thickness of a NACA airfoil section?

In the example P=4 so the maximum camber is at 0.4 or 40% of the chord. XX is the thickness divided by 100. In the example XX=12 so the thiickness is 0.12 or 12% of the chord. The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber line.

What is the 4 digit code for airfoil?