[DesignModeler] Inaccurate drawing of Airfoil using 3d curve concept

ajitmenezes · May 16, 2014, 04:42

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....

khoopes · May 16, 2014, 15:36

Worked just fine for me. Granted I am using 15.0

ttnico · May 22, 2014, 14:59

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

ttnico · May 24, 2014, 11:51

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?

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Problem with airfoil shape optimization	robyTKD	SU2 Shape Design	7	March 7, 2022 16:18
Problem with restart solution in shape_optimization.py	robyTKD	SU2 Shape Design	21	May 29, 2013 09:26
[ICEM] 2D Airfoil Patch Dependent Mesher Ignores Curve Sizing	khoopes	ANSYS Meshing & Geometry	0	February 2, 2013 10:28
airfoil drawing in ansys workbench	Hammam	ANSYS Meshing & Geometry	2	June 18, 2011 19:34
CFX4.3 -build analysis form	Chie Min	CFX	5	July 12, 2001 23:19

May 16, 2014, 15:36		#2
khoopes Member Kevin Hoopes Join Date: Oct 2010 Posts: 43 Rep Power: 16	Worked just fine for me. Granted I am using 15.0

May 22, 2014, 14:59		#3
ttnico 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

May 24, 2014, 11:51		#4
ttnico 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?