Short to say: at the end we have been not succesfull.

Together with a friend - because I have no clue in programming - we tryed to handle with lines and points to get koordinates and a sorting of lines to the right points. Prepairing structures for framework analysis. Since a longer time I know that moi has a big potential as cad program for aircraft development.

It is exactly what I need for a real aircraft projekt that I plane to build in my Thank you for the NACA skript that you have made. 'NACAAirfoilGenerator ordinates vs airfoils-.png NACAAirfoilGenerator-.PNG NACAAirfoilGenerator ordinates vs airfoils-.zip That kept me pretty busy for quiet a while.Īs ever, any feedback - especially bug reports - is always appreciated. I'll make a post about how the thickness distribution curve for the 43012A was generated with an additional reverse-action script another day. Conversely, generating more than 100 stations doesn't appear to yield much if any noticeable improvement. Generating airfoils with less than 60 chord-wise stations is not recommended as the airfoil's curvature smoothness, when checked with a curvature analysis tool, reduces noticeable. TODO: Implement four-digit modified, five-digit modified, and six-digit series - contains working (public domain) code likely worth incorporating. Input parameter validation is rudimentary where it has been implemented. Five-digit airfoils with reflex camber lines are not yet implemented.Ī4 coefficient (slider) value input can be set by user 'out of NACA limits'. As you can see though, output from the script appears to be a reasonable match to the ordinates for the above mentioned airfoils at least: * 'verified' is probably not the best word, as errors are known to exist in the original NACA ordinate data. NACAAirfoilGenerator ordinates vs airfoils-.3dm in the attached zip. Conformity of output with official NACA ordinates has been verified* for NACA 0012, 6518, 23012, 43012 & 43012A, see file: Variable thickness trailing edge (T.E) implemented. Now generates all 'basic' NACA four-digit and five-digit series airfoils, including 43012A. camber_line ( x = 0.5 ) 0.Here's the latest NACAAirfoilGenerator script with various minor and a few major improvements since first release: Linear interpolation between two different airfoils ( MorphAirfoil)Įxample > from airfoils import Airfoil > foil = Airfoil. Interpolation or computation of airfoil geometry parameters Image in the public domain, via Wikimedia Commons.Īirfoil generation with a NACA-4 series definitionįull support for airfoils from the UIUC Airfoil Coordinates Database An airfoil object is defined by upper and a lower surface coordinates.Īirfoil nomenclature. The library provides tools to easily instantiate airfoil objects and to query geometric information. Airfoils is a small Python library for object-oriented airfoil modelling.

Airfoil profile generator software