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. Furthermore, it enables the cruise performance and drag divergence Mach number to be predicted with only one simulation of the cruise point, which will greatly save the computational cost of optimizations.It’s working really well for me. It indicates that the drag divergence Mach number can be increased by obtaining a shock wave that is further upstream in the detailed design. Compared with Korn's equation, the discovered correlation reduces the maximum prediction error by approximately 40%. A new linear correlation is discovered and validated by existed airfoil databases. Correlation screening and multivariate regression are carried out to discover knowledge about the airfoil drag divergence Mach number and pressure distribution features. This paper designs a supercritical airfoil database that covers the typical free stream Mach number, angle of attack, lift coefficient, and geometry of modern transonic commercial aircraft. However, it neither reveals the key factors of fluid features on the drag divergence nor contributes to the detailed design. It is very helpful in the aircraft initial design. For example, Korn's equation predicts the airfoil drag divergence Mach number using the airfoil maximum thickness and the lift coefficient. Aerodynamic rules and knowledge are often obtained through theoretical research and experiments, which have contributed greatly to aircraft design.
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