The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber.
#Naca airfoil generator 6 series#
Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. 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.
#Naca airfoil generator 6 code#
The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties. The shape of the NACA airfoils is described using a series of digits following the word "NACA". The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). thickness 5: Camber 6: Upper surface 7: Trailing edge 8: Camber mean-line 9: Lower surface Profile lines – 1: Chord, 2: Camber, 3: Length, 4: Midline A: blue line = chord, green line = camber mean-line, B: leading-edge radius, C: xy coordinates for the profile geometry (chord = x axis y axis line on that leading edge) Wing shape Profile geometry – 1: Zero-lift line 2: Leading edge 3: Nose circle 4: Max.