![]() Not to draw conclusions I haven't quite had a chance to look at it yet. Out of curiosity, does it use the xfoil engine as a LGPL library? Xfoil ( ) is GPL'd free software, so linking proprietary code against it or selling it, without source code, for anything but the cost of distributing it would be a breach of the licensing agreement. I can't seem to get to the page with the URL given I get an error page from Lycos in Italian and am then redirected to the Lycos main page. In addition, XFoil's processing parameters can be modified via a Windows menu. Basically, Profili delivers the power of XFoil in a user-friendly format, coupled to an extensive airfoil database. Mark Drela, professor of Aero / Fluids at MIT, whose research specialty is computational aerodynamics. Now, priced at $10, you're probably thinking "The analysis capability can't be very sophisticated," however consider that the analysis engine built into Profili is the well-known XFoil program by Dr. Here's a standard polar of 5 airfoils at Re = 70000, predicting low-Re breakdown of the E387 & Zagi 12. No doubt Profili will continue to evolve, but this version 2 marks a huge refinement over the previous version dealing with airfoil geometry alone.īelow are a couple Profili outputs (I pasted the legend it actually appears above the charts). Given the complexity of CFD analyses, even if not highly accurate in terms of actual numbers, the results can be insightful for comparative purposes, or to see effects of modified airfoil geometries, different Re, etc. Just a few mouseclicks generates not only standard polars, but multi-airfoil comparison plots, or plots of various combinations of Cl, Cd, Cl/Cd, Cm, AOA, Re. change camber, thickness, etc), or for any custom airfoil per user-entered coordinates. The author, Stefano Duranti, has released a new version (latest is 2.03d as of this writing) that will generate polars for any of the 2200+ airfoils in its database (which can all be modified, e.g. This will be an exception, as I'll give credit where it's due (I have no affiliation to the product / person).Īnyone designing model aircraft, or otherwise interested in airfoil selection and performance comparisons, should look at Profili 2.0 (and its price => $10 ) The minimum drag will be around Cl=1.1 and the maximum lift to drag coefficient will be around CI/Cd=52 at 4-5Ĭl 1.6 1.4 1.2 1.0 0.8 0.6 0.4 0.2 Cd 0+ O- 0.05 0.10 0.Normally I don't go around playing "salesman" touting a particular product. We obtain the following graph results for the behavior of the airfoil: ci -1.6 -1.4 -1.2-1.0 0. 15.0 As we can see for an angle of attack from 1 to 4 it can fly in optimum conditions.Ĭm vs Alpha Alpha cm -10.0 10.0 15.0 -0.02 -0.04 0.08 -0.10 0.12 -0.14 For the range of angles of attack analyzed (-11 to 11) we can see that the airfoil is stable.Ĭl/Cd vs Alpha d/cd Alpha -10.0 -5.0 5.0 10.0 15.0Ģ.6 NACA 8415 For the final airfoil test we are using NACA 8415. 0/08 0.30 0.12 0.14 0.2 We can appreciate how our minimum drag will be around Cl=0.8 and the maximum liftto drag coefficient will be around Cl/cd=1.7Ĭl vs Alpha $ 1.2 1.0 26 14 2.2 Alpha -10.0 20. We obtain the following graph results for the behavior of the airfoil: Cl vs CD 14 1.2 10 0.8 0.6 0.2 cd 0.02 0.04 0.06. NACA6412 For the second airfoil test we are using NACA 6412. Using XFLRS and the following data we have analyzed different airfoils. ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |