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Old   June 26, 2007, 13:04
Default NACA0012 geometry/design software needed
  #1
Franny
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Hi, I am looking for an accurate model of the NACA0012 airfoil compatible with Solidworks or Ansys Workbench.I am tring to build it using the coordinates but i need to have at least 50 points on the lower and 50 points on the upper surface to generate an adequate curve especially close to the leading edge and the trailing edge.I have already exported the coordinated from the NACA library,but when I import them in Solidworks it looks like the two surfaces do not join at the trailing edge.Anyone can suggest any airfoil design software available online in which i can define the number of points along the airfoil surface? Thank you.

Franny
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Old   June 26, 2007, 15:42
Default Re: NACA0012 geometry/design software needed
  #2
TITAN Algorithms
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http://www.basiliscus.com/ProaSectio...xD/TableD1.txt
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Old   June 26, 2007, 15:43
Default Re: NACA0012 geometry/design software needed
  #3
TITAN Algorithms
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sorry, I see the points don't merge here as well. Perhaps you could digitize the shape.

DSS
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Old   June 26, 2007, 16:44
Default Re: NACA0012 geometry/design software needed
  #4
TITAN Algorithms
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I just cut an STL model of this cross section. It seems pretty accurate and the endpoints are connected. I can send it if you want.
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Old   June 26, 2007, 16:46
Default Re: NACA0012 geometry/design software needed
  #5
Jonas Larsson
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If I remember correctly the naca 4 digit series have a certain trailing edge thickness, hence the upper and lower surfaces will not meet exactly at the trailing edge. There are variants with a zero trailing edge thickness and there are variants with a selectable thickness, but if you want the original naca 0012 geometry it will have a ceratin fixed trailing edge thickness.
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Old   June 27, 2007, 00:59
Default Re: NACA0012 geometry/design software needed
  #6
Markus Lummer
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http://naca.central.cranfield.ac.uk/...report-460.pdf
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Old   June 28, 2007, 03:32
Default Re: NACA0012 geometry/design software needed
  #7
Charles
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Easy way to generate airfoil coordinates for NACA 4 and 5-digit series is XFoil. You can adjust the trailing edge thickness to whatever you desire.

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Old   June 28, 2007, 04:40
Default Re: NACA0012 geometry/design software needed
  #8
Franny
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Hi Titan Algorithms, I didnt have a chance to answer you yesterday,but it would be nice if you send the model i can have a look at it. My email address is k0433072@kingston.ac.uk I really appreciate your helo.

Franny
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Old   June 28, 2007, 04:44
Default Re: NACA0012 geometry/design software needed
  #9
Franny
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Hi , this is why in my initial simulation,where the model used was adequate but with too few points along the surface,the pressure/coeff pressure distribution ,had a strange peak on the trailing edge! Thank you for the int! Regards Franny
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Old   June 28, 2007, 13:11
Default Re: NACA0012 geometry/design software needed
  #10
TITAN Algorithms
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Franny

I clipped the 3D STL into one z-Segment. Hopefully it will fit here. The trailing edge is stitched up:

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Old   June 29, 2007, 03:28
Default Re: NACA0012 geometry/design software needed
  #11
saygin
Guest
 
Posts: n/a
This is NACA0012 data that I extracted from MeshPilot program -i guess the program was that, it was some long time ago-. The trailing edge has no thichness. Hope it helps.

Saygin

-------------------------------------------------------

0.100000000000000E+01 0.000000000000000E+00

0.999614518000000E+00 -0.544672999000000E-04

0.998458667000000E+00 -0.217631273000000E-03

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0.993844170000000E+00 -0.866738829000000E-03

0.990392640000000E+00 -0.134987575000000E-02

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0.936248004000000E+00 -0.867327229000000E-02

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0.915734806000000E+00 -0.113283142000000E-01

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0.892658465000000E+00 -0.142409002000000E-01

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0.635720225000000E+00 0.417490475000000E-01

0.654508497000000E+00 0.400478310000000E-01

0.673058529000000E+00 0.383166466000000E-01

0.691341716000000E+00 0.365617557000000E-01

0.709329869000000E+00 0.347892879000000E-01

0.726995250000000E+00 0.330052474000000E-01

0.744310621000000E+00 0.312155228000000E-01

0.761249282000000E+00 0.294258983000000E-01

0.777785117000000E+00 0.276420659000000E-01

0.793892626000000E+00 0.258696373000000E-01

0.809546975000000E+00 0.241141560000000E-01

0.824724024000000E+00 0.223811065000000E-01

0.839400373000000E+00 0.206759225000000E-01

0.853553391000000E+00 0.190039913000000E-01

0.867161255000000E+00 0.173706557000000E-01

0.880202983000000E+00 0.157812112000000E-01

0.892658465000000E+00 0.142409002000000E-01

0.904508497000000E+00 0.127549011000000E-01

0.915734806000000E+00 0.113283142000000E-01

0.926320082000000E+00 0.996614304000000E-02

0.936248004000000E+00 0.867327229000000E-02

0.945503262000000E+00 0.745444229000000E-02

0.954071587000000E+00 0.631422093000000E-02

0.961939766000000E+00 0.525697329000000E-02

0.969095668000000E+00 0.428682981000000E-02

0.975528258000000E+00 0.340765371000000E-02

0.981227618000000E+00 0.262300840000000E-02

0.986184960000000E+00 0.193612572000000E-02

0.990392640000000E+00 0.134987575000000E-02

0.993844170000000E+00 0.866738829000000E-03

0.996534228000000E+00 0.488780719000000E-03

0.998458667000000E+00 0.217631273000000E-03

0.999614518000000E+00 0.544672999000000E-04

0.100000000000000E+01 0.000000000000000E+00

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Old   June 30, 2007, 04:43
Default Re: NACA0012 geometry/design software needed
  #12
Franny
Guest
 
Posts: n/a
Thank you very much Saygin.I ve build it up the airfoil in solidworks and i will use it to simulate the flow in CFX.It looks a lot better of the one I had as is defined by much more points. Thanks again.

Franny
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Old   June 30, 2007, 04:46
Default Re: NACA0012 geometry/design software needed
  #13
Franny
Guest
 
Posts: n/a
Hi, thank you very much for your help.I will try to use your coordinates. Very kind of you.

Thank you again.

Franny
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Old   July 7, 2007, 15:57
Default Re: NACA0012 geometry/design software needed
  #14
John Chawner
Guest
 
Posts: n/a
Here are two more options.

UIUC Airfoil Coordinates Database:

http://www.ae.uiuc.edu/m-selig/ads/c...atabase.html#N

DesignFOIL software:

http://www.dreesecode.com/
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