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#NACA 6 DIGIT AIRFOIL GENERATOR CODE#
#NACA 6 DIGIT AIRFOIL GENERATOR SERIES#

"a=" followed by a decimal number describing the fraction of chord over which laminar flow is maintained.Two digits describing the maximum thickness in tens of percent of chord.One digit describing the lift coefficient in tenths.

#NACA 6 DIGIT AIRFOIL GENERATOR 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.

One letter referring to a standard profile from the earlier NACA series. Only Register an Account to DownloadNaca 4415 Airfoil Data PDF.

One digit describing the distance of the minimum pressure area on the lower surface in tens of percent of chord.

One digit describing the distance of the minimum pressure area on the upper surface in tens of percent of chord.

If you look in The Theory of Wing Sections, there are plots of the chordwise loading provided by different mean lines (camber lines). 2) Chordwise loading is indeed mean line shape. 1) The subscript number has no influence on the airfoil shape description is thus often dropped.

#NACA 6 DIGIT AIRFOIL GENERATOR SERIES#

The airfoil is described by seven digits in the following sequence: RE: Naca 6 Series Airfoil Question 10879353. Further advancement in maximizing laminar flow achieved by separately identifying the low pressure zones on upper and lower surfaces of the airfoil.