- NACA AIRFOIL GENERATOR 6 FULL VERSION
- NACA AIRFOIL GENERATOR 6 SOFTWARE
- NACA AIRFOIL GENERATOR 6 CODE
NACA AIRFOIL GENERATOR 6 CODE
The following table presents the various camber-line profile coefficients:įour- and five-digit series airfoils can be modified with a two-digit code preceded by a hyphen in the following sequence: The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is y t = 5 t, Plot of a NACA 0015 foil generated from formula The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.Įquation for a symmetrical 4-digit NACA airfoil The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. įor 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.
Engineers could quickly see the peculiarities of each airfoil shape, and the numerical designator ("NACA 2415," for instance) specified camber lines, maximum thickness, and special nose features. 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. According to the NASA website:ĭuring the late 1920s and into the 1930s, the NACA developed a series of thoroughly tested airfoils and devised a numerical designation for each airfoil - a four digit number that represented the airfoil section's critical geometric properties. NACA initially developed the numbered airfoil system which was further refined by the United States Air Force at Langley Research Center.
The only difference is that it analyzes NACA Airfoils and it will not import other airfoil shapes.
NACA AIRFOIL GENERATOR 6 FULL VERSION
VisualFoil NACA is similar to the full version of VisualFoil 5.0.
NACA AIRFOIL GENERATOR 6 SOFTWARE
The software accurately computes lift, drag, moments for NACA 4, 5 and 6-series airfoils. It is based on a linear strength Vortex panel method coupled with a boundary layer solver. VisualFoil NACA is a NACA airfoil generator and airfoil analysis software package.