#Naca 6 digit airfoil generator series
Compute the mean camber line coordinates using the same equations provided for the Four- or Five-Digit Series as appropriate. As you suggest in your questions, the early NACA airfoil series, the 4-digit, 5-digit, and modified 4-/5-digit, were generated using analytical equations that describe the camber (curvature) of the mean-line (geometric centerline) of the airfoil section as well as the sections thickness distribution along the length of the airfoil. Pick values of x from 0 to the maximum chord c. To compute the coordinates for a modified airfoil shape: 1. Instead of the maximum thickness being located at 40% chord, the position on this airfoil is at 40.69% chord. Instead of being 3% thick, this airfoil is 3.46% thick. These merely indicate slight adjustments to the maximum thickness and location thereof. Finally, notice that the 0003.46-64.069 features two sets of digits preceeded by decimals. In this example, the location of maximum thickness has been moved back to 40% chord.
The default location for all four- and five-digit airfoils is 30% back from the leading edge. The second digit determines the location of maximum thickness in tenths of chord.
Increasing this value specifies an increasingly more rounded nose. 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. The first digit following the dash refers to the roundedness of the nose. The first modification we will consider is the 0003-64. This shape is a symmetrical airfoil that is identical above and below the mean camber line. The basic shape is the 0003, a 3% thick airfoil with 0% camber. Let us consider the root section, the NACA 0003.46-64.069, as an example. The airfoil sections you mention for the B-58 bomber are members of the Four-Digit Series, but the names are slightly different as these shapes have been modified.
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