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[DesignModeler] Inaccurate drawing of Airfoil using 3d curve concept |
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#1 |
New Member
Ajit Menezes
Join Date: May 2014
Posts: 1
Rep Power: 0 ![]() |
Hi, I'm new here, and new to using Ansys Workbench as well. I have tried to import a NACA4412 airfoil on the DesignModeller section using the 3D curve function and a .txt file (coordinates.txt, attached below). However, the curve generated has a few bumps and straight lines, and I am unsure of how to rectify it. Image of the issue in PDF is also attached below.
Would be really grateful for some help! Sorry if the question may be abit amateurish.... |
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#2 |
Member
Kevin Hoopes
Join Date: Oct 2010
Posts: 43
Rep Power: 16 ![]() |
Worked just fine for me. Granted I am using 15.0
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#3 |
New Member
turan
Join Date: May 2014
Posts: 3
Rep Power: 12 ![]() |
khoopes why this airfoil is open at the sharp end,how can I closed ? my problem is different,when I choose
Concepts-Surface form Edges I get this error Some selected edges failed to form closed loops I am using this amazing site https://confluence.cornell.edu/displ...oil+-+Geometry here is my airfoil 1 1 1,00000 0,00021 0,00000 1 2 0,95053 0,01028 0,00000 1 3 0,90104 0,02038 0,00000 1 4 0,85148 0,03018 0,00000 1 5 0,80151 0,03967 0,00000 1 6 0,75126 0,04780 0,00000 1 7 0,70108 0,05480 0,00000 1 8 0,65085 0,06106 0,00000 1 9 0,60057 0,06624 0,00000 1 10 0,55025 0,07040 0,00000 1 11 0,49989 0,07344 0,00000 1 12 0,44950 0,07522 0,00000 1 13 0,39910 0,07552 0,00000 1 14 0,34871 0,07414 0,00000 1 15 0,29834 0,07131 0,00000 1 16 0,24800 0,06705 0,00000 1 17 0,19770 0,06126 0,00000 1 18 0,14748 0,05366 0,00000 1 19 0,09737 0,04380 0,00000 1 20 0,07230 0,03865 0,00000 1 21 0,04749 0,03034 0,00000 1 22 0,02276 0,02095 0,00000 1 23 0,01059 0,01451 0,00000 1 24 0,00582 0,01112 0,00000 1 25 0,00350 0,00902 0,00000 1 26 0,00000 0,00000 0,00000 1 27 0,00650 -0,00678 0,00000 1 28 0,00918 -0,00796 0,00000 1 29 0,01441 -0,00969 0,00000 1 30 0,02724 -0,01251 0,00000 1 31 0,05251 -0,01592 0,00000 1 32 0,07770 -0,01919 0,00000 1 33 0,10263 -0,01996 0,00000 1 34 0,15252 -0,02244 0,00000 1 35 0,20230 -0,02406 0,00000 1 36 0,25200 -0,02499 0,00000 1 37 0,30166 -0,02537 0,00000 1 38 0,35129 -0,02518 0,00000 1 39 0,40090 -0,02436 0,00000 1 40 0,45050 -0,02266 0,00000 1 41 0,50011 -0,02024 0,00000 1 42 0,54975 -0,01736 0,00000 1 43 0,59943 -0,01418 0,00000 1 44 0,64915 -0,01086 0,00000 1 45 0,69892 -0,00760 0,00000 1 46 0,74874 -0,00460 0,00000 1 47 0,79849 -0,00229 0,00000 1 48 0,84852 -0,00132 0,00000 1 49 0,89896 -0,00076 0,00000 1 50 0,94947 -0,00048 0,00000 1 51 1,00000 -0,00021 0,00000 |
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#4 |
New Member
turan
Join Date: May 2014
Posts: 3
Rep Power: 12 ![]() |
when I change firts and last line
1 1 1,00000 0,00000 0,00000 and last line 1 0 its closed,probably results will be effected but this small change can be negligible,isnt it? |
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Tags |
3d curve, airfoil, ansys, design modeller |
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