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Parametric Multi-Element


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#1 Mr. Christian Anzalotta

Mr. Christian Anzalotta

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Posted 22 January 2020 - 06:07 AM

So I followed tutorials to import my IGES geometry, import the airfoil data points and also parametrize the curves via scaling/translation/rotation. This allows me to use the pre-existing geometry as references and create the airfoils within Caeses. Now I am interested in parametrizing the generated FImageCurves of one of the multi-elements and optimizing the airfoil profile (so the actual FImageCurve).

 

What tutorial/example can guide me next in setting up the parametrization of a pre-existing airfoil's profile similar in setup to the "Mapping Adjoint Sensitivities to Geometry Parameters" Caeses post where the automotive company has access to camber and thickness controls? My end goal being where I parametrize a pre-existing airfoil, the raw data points ARE available and have been imported as an FImagecurve and now controls are implemented.

 

Cannot show the full cad so I attached image with dummy single airfoil that was imported using raw data points and using the feature for creating image curve for reference.

Attached Thumbnails

  • example.JPG

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#2 Ceyhan Erdem

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Posted 22 January 2020 - 10:45 AM

Hi Christian,

 

What you you have to do first is to redefine the airfoil curve as a combination of thickness distribution and camber distribution curves.

Parameterizing these two curves in an automated way would provide you a way to approach your goal.

 

Let me prepare a simple project where one can read point cloud data; convert it to an interpolation curve; redefine it as camber distribution and thickness distribution curves and finally parameterize those curves in a simple and easy way.

 

If I find time today, will be posting here.

 

Cheers

Ceyhan


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#3 Ceyhan Erdem

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Posted 22 January 2020 - 11:56 AM

Hi Christian,

 

Please find the attached project.

Please note that this is rather a simple case that can further be improved.

 

Please let me know if you have further questions.

 

The feature that reads the point data needs a file where x y z coordinates are provided only. You can modify the feature with respect to your needs.

 

Cheers

Ceyhan

Attached Files


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#4 Mr. Christian Anzalotta

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Posted 22 January 2020 - 07:44 PM

Thank you for the file. I am running through the file to better understand the setup, etc so I used this dat file which I can provide.

 

I tried using two other .dat files I generated in the format you mentioned, but seems to have some error when solving for the pXmax and camberline/thickness. Let me know if you find a solution before me!

 

Currently, I'm attempting to use the definitions you had within the file you sent and implementing into my current sim where the airfoils aren't have issue in generating the imported FImagecurve.  Thank you for the quick setup and advice as well very helpful I can see myself generating designs by the end of the night or tomorrow at this pace.

 

Update: Thank you it has implemented the airfoil I added the appropriate Z column data and worked flawlessly.

 

Update2: Now only concern is the leading/trailing edge and the updated PS had a minor issue. Let me know what you think could be the issue. 


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Attached Thumbnails

  • yes.JPG
  • yes2.JPG
  • PS.JPG

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#5 Ceyhan Erdem

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Posted 23 January 2020 - 09:16 AM

Hi Christian,

 

When I deal with an airfoil I always start with one that has a chord length of 1.

So in most databases the airfoil point data has an aligned chord to x-axis that has a length of 1, starting from 0 and ending at 1.

 

You can either modify the feature "parameterize curve" to fit into your dimensions, or scale the airfoil data so that it has a chord of 1 and aligned to x axis.

 

Cheers

Ceyhan


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#6 Ceyhan Erdem

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Posted 23 January 2020 - 09:19 AM

Please find below the point cloud data that I have used. As I said you can modify the "ReadData" feature Definition wrt your needs.

 

  1.000000  0.000000  0.000000
  0.950200  0.008912  0.000000
  0.900500  0.017584  0.000000
  0.850700  0.026352  0.000000
  0.800800  0.035078  0.000000
  0.750500  0.043616  0.000000
  0.700900  0.051586  0.000000
  0.650800  0.059006  0.000000
  0.600600  0.065628  0.000000
  0.550300  0.071270  0.000000
  0.500000  0.075742  0.000000
  0.449600  0.078800  0.000000
  0.399200  0.080180  0.000000
  0.348800  0.080320  0.000000
  0.300000  0.078760  0.000000
  0.250000  0.076000  0.000000
  0.200000  0.071660  0.000000  
  0.175000  0.068800  0.000000  
  0.150000  0.065400  0.000000
  0.125000  0.061386  0.000000
  0.100000  0.056496  0.000000
  0.075000  0.050484  0.000000
  0.050000  0.042726  0.000000            
  0.037500  0.037762  0.000000  
  0.025000  0.031500  0.000000
  0.012500  0.022728  0.000000
  0.005000  0.014580  0.000000
  0.002000  0.009474  0.000000
  0.000000  0.000000  0.000000
  0.002000 -0.005484  0.000000
  0.005000 -0.008754  0.000000
  0.012500 -0.013108  0.000000
  0.025000 -0.017282  0.000000
  0.037500 -0.020250  0.000000
  0.050000 -0.022680  0.000000
  0.075000 -0.026610  0.000000
  0.100000 -0.029720  0.000000
  0.125000 -0.032260  0.000000
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  0.250000 -0.039360  0.000000
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  0.348800 -0.039420  0.000000
  0.399200 -0.037900  0.000000
  0.449600 -0.035574  0.000000
  0.500000 -0.032588  0.000000
  0.550300 -0.029338  0.000000
  0.600600 -0.025976  0.000000
  0.650800 -0.022670  0.000000
  0.700900 -0.019420  0.000000
  0.750500 -0.016202  0.000000
  0.800800 -0.012994  0.000000
  0.850700 -0.009776  0.000000
  0.900500 -0.006536  0.000000
  0.950200 -0.003272  0.000000
  1.000000  0.000000  0.000000

 


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