currently only created as in the 'open' style (as described by NACA).Ī line segment closes the otherwise open T.E., however it and the airfoil
#AIRFOIL GENERATOR 5 DIGIT PDF#
Output has NOT YET BEEN VERIFIEDĪgainst official NACA ordinates available in the pdf documents below.
This version only generates a NACA five-digit series airfoil and Release notes copied here for convenience:
Here's the first release of the NACA Airfoil Generating script :) I'd be interested to discuss it some more, after I post the script so far. Or it may be easier still and just as good/accurate just to store ordinates of a best-fit to points, faired NURBS curve. But I wonder if log aesthetic curve segments might fit even better. I've already created a 14 coefficient, almost oscillation-free, polynomial to describe the 43012A thickness distribution (using to do some pretty cool interactive regression), and it's a pretty close fit. Even the seminal NACA Technical Report 610 of 1936 only talks of "filling out the concave portion of the lower surface near the nose of the NACA 43012 airfoil and thickening the upper surfaces so that the mean line is unchanged". It has it's very own thickness distribution that was never formalised by any equation certainly none that I can find. It would be an interesting exercise to try out though and not difficult.Īs I said, I'm glad you spotted this thread because I'd be interested to see if some of the work you've done on generating some of the more specialised (spiral) curves might be applied to describing the thickness-distribution of NACA's five-digit series airfoil odd-ball: the 43012A. I did think about calculating the airfoil upper surface curve in reverse order, and then adding the lower surface curve, but gave up on it as wasteful to do a moderately complex and identical airfoil thickness distribution calculation twice.
#AIRFOIL GENERATOR 5 DIGIT FULL#
Please do take a look when I post the full initial script later today. I'm pretty certain the index numbering isn't causing any problems.
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