What do the numbers in NACA mean?

What do the numbers in NACA mean?

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 does NACA 4412 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].

Is NACA legit?

NACA is a nonprofit and HUD-certified homeownership and advocacy organization that is committed to assisting economically disadvantaged individuals with becoming homeowners by offering loans at below-market interest rates with no down payment or closing costs.

What is a NACA 1234 airfoil?

For example, the NACA 1234-05 is a NACA 1234 airfoil with a sharp leading edge and maximum thickness 50% of the chord (0.5 chords) from the leading edge. In addition, for a more precise description of the airfoil all numbers can be presented as decimals.

What is the difference between NACA 2412 and 0012?

For example, a NACA 2412 airfoil uses a 2% camber (first digit) 40% (second digit) along the chord of a 0012 symmetrical airfoil having a thickness 12% (digits 3 and 4) of the chord. The NACA five-digit series describes more complex airfoil shapes.

What is the maximum camber of NACA 2412 airfoil?

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 23112 profile?

For example, the NACA 23112 profile describes an airfoil with design lift coefficient of 0.3 (0.15*2), the point of maximum camber located at 15% chord (5*3), reflex camber (1), and maximum thickness of 12% of chord length (12).