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The second digit is twice the longitudinal location of the maximum camber location (in 10ths). The first digit is 2/3 of the design lift coefficient (in 10ths). For a 230 camber-line profile (the first 3 numbers in the 5 digit series), is used.Ĭamber line profiles 3 digit camber lines ģ digit camber lines provide a very far forward location for the maximum camber. Finally, constant is determined to give the desired lift coefficient. The constant is chosen so that the maximum camber occurs at for example, for the 230 camber-line, and. Where the chordwise location and the ordinate have been normalized by the chord.
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The camber-line is defined in two sections:
AIRFOIL DESIGN CHARACTERISTICS SERIES
The NACA five-digit series describes more complex airfoil shapes: įor 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).
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The equation for a cambered 4-digit NACA airfoil The leading edge approximates a cylinder with a radius of: to −0.1036) will result in the smallest change to the overall shape of the airfoil. If a zero-thickness trailing edge is required, for example for computational work, one of the coefficients should be modified such that they sum to zero. Note that in this equation, at ( x/ c) = 1 (the trailing edge of the airfoil), the thickness is not quite zero.
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The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. The NACA four-digit wing sections define the profile by: 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. 1.2 The equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.