![]() I’m not getting notifications on updates to this thread. Most certainly… I don’t assume to know what the OP’s design intention is here, whether it’s simply to get something that looks clean and correct or if it’s intended to be functional. Only that one b737a.dat airfoil comes out wonky, and reconfirmed that the points are simply in the wrong location for a fair curve to exist.Īirfoil doodling: Test Airfoils.3dm (78.1 KB) Here is batch of tests firing off a wide variety of options from the aerospace community and using the new functionality of curve knot options. dat that the user is browsing? This would be slow on older Macs since the script would essentially be running on every set of coordinates that the user single-clicks on in the start dialog, though I’m genuinely curious what your thoughts are on the matter. Is there any way to generate a preview pane drawing of the. ![]() Here is a pipe dream since I imagine this is CPU-intensive and probably would require a lot of time to write, though I do not know for certain. Extend Trailing Edge (extend, trim, close curve, delete orphaned segments) again if the TE curve is open.Interpolate Trailing Edge (if the generated curve is open).Close trailing Edge curve (add a line between the first upper TE and first lower TE points if the generated curve is open).dat natively (just how the script functions now) If you are curious to refine this script and have the time to dedicate to doing so, I would propose the options to: The latter approach may lead to deformed trailing edges when the airfoils have dramatic undercamber or other complexities, though if you don’t mind, it would be fun to play with as script command. It can be done manually thinking off of past experience by extending curves until they intersect, trimming one with the other, then joining them, or doing a simple interpolation (think reading the coordinates all the way around in a circle). dat files–to the right of imported airfoil, should allow for that. Having a trailing edge curve project to a finite point–in the case of these. It’s by no means necessary as one can just grab the endpoints and join them with a line, though it could help in the case of how Rhino deals with generating blended section fillets which is to say that it has problems when the math isn’t correct. ![]() If that is not a lot to ask as a feature built into the code, it would be icing on the cake. That is fantastic, and has me thinking that I will start learning how to write these, because so many batch operations that I’ve done in the past to say, build out a wing and then slice it into intermediate wing sections, could be performed with some basic knowledege of the language (though that does take some of the fun out of modeling in Rhino).Īs far as any future features, it might be helpful to have the option to close the trailing edge on some of these sections. Thanks a lot for teaching me how to point Rhino at your script from within command line. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application.It’s working really well for me. Available data on high-lift devices are presented. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. Summary of Airfoil Data The historical development of NACA airfoils is briefly reviewed.
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