(For detailed explanation about these equations, please check out our previous post about NACA 4 Digit Airfoil) MATLAB Code: Let us move to the part where the real fun lies, THE MATLAB.The theoretical drag of the airfoil can be estimated by making a flat plate assumption and analyzing the laminar and turbulent cases Geometrical Analysis NACA has a nomenclature for 4-digit airfoils.
#5 DIGIT AIRFOIL GENERATOR CODE#
![5 digit airfoil generator 5 digit airfoil generator](https://tracfoil.com/airfoils/uploads/images/gnacalt/gnacalt_E.jpg)
There are also different equations for standard and reflex camber lines.
#5 DIGIT AIRFOIL GENERATOR SERIES#
The equation for the camber line is split into two sections like the 4 digit series but the division between the two sections is not at the point of maximum camber. The maximum thickness as percentage.In the examble XX=12 so the maximum thickness is 0.12 or 12% chord. In the examble P=3 so maximum camber is at 0.15 or 15% chordĠ = normal camber line, 1 = reflex camber line The position of maximum camber divided by 20. It indicates the designed coefficient of lift (Cl) multiplied by 3/20. NACA 5 digit airfoils in the database NACA 22112 NACA 23012 NACA 23015 NACA 23018 NACA 23021 NACA 23024 NACA 23112 NACA 24112 NACA 25112 Design coefficient of lift