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https://github.com/wyllduck/openfoam-toolchain-helperfunctions

WARR thermal simulation
https://github.com/wyllduck/openfoam-toolchain-helperfunctions

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WARR thermal simulation

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README 

        
# Helper Functions - OpenFOAM-ToolChain-for-Rocket-Aerodynamic-Analysis

__by Félix Marti Valverde__



This repository is part of a greater project found in the main repository _OpenFOAM ToolChain for Rocket Aerodynamic Analysis_ (https://github.com/WyllDuck/OpenFOAM-ToolChain-for-Rocket-Aerodynamic-Analysis). The functions contained here are miscellaneous calculations and data extraction scripts to validate the CFD methodology followed in the main repository.





  Image 2

  Image 1




### links



* __SIMULATIONS FILES:__ https://1drv.ms/f/s!AhNN3_xNz6xdhe1IEGJ-niuFxb3V3g?e=uLhchQ



* __REPORT:__ https://1drv.ms/b/s!AhNN3_xNz6xdhex7se7BjiaeyGrojg?e=m3ClFa



* __CAD FILES:__ https://1drv.ms/f/s!AhNN3_xNz6xdhK0CDDJZs5zly81P_w?e=NSELu2



## SETUP



Install all the requiered python libraries 

```bash

python3 -m pip install -r requirements.txt

```



## EXECUTION



To obtain the configuration files to template the OpenFOAM workspace all the data must be generated from scratch. Follow these steps to create it:



1. Calculate the boundary conditions for the simulations



```bash

python3 get_boundary_conditions.py

```



2. Extract the aerodynamic coefficients from the graphs



```bash

python3 picture2coefficients.py

```



3. Generate the templating files. This Python script is configurable, edit the parameter inside the script to generate the _JSON_ files you require.



```bash

python3 get_configuration_files.py

```



## CONTENT



### FOLDERS



    

      
  • 

    data: PDFs containing only the relevant wind-tunnel graphs used to validate the CFD results. Data comes from sources [1][2].
    • 

      

      
  • 

    graph: All the pages contained in the pdf from data are converted to JPEG images, to then proceed to data digitalization using Python scripts.
    • 

      

      
  • 

    paper_plots: This folder only contains Python scripts used to generate the plots in the report. Click on the link above to access the report.
    • 

      

      
  • 

    paraview_states_plots: This folder contains the Paraview state files used to post-process CFD results in the report in addition to the raw images added in the report. Click on the link above to access the report.
    • 

      

      
  • 

    points: Contains a set of TXT files with information to extract each plot with the aerodynamic coefficient from the image in graphs.
    • 





### SCRIPTS



    

      
  • 

    picture2coefficients.py: Uses spline lines to extrapolate the data from the TXT file in points folder, thus covering all relevant angles of attack. Additionally, a folder named check_images is generated containing 2 images per graph. One overlaying the TXT information to the original image in graphs to check for user input mistakes, and another image with the generated spline data points.
    •   
    


      
  • 

    get_boundary_conditions.py: Calculates the different boundary conditions required for each Mach Number to keep a constant Reynolds number.
    • 

      

      
  • 

    atmosphere.py: Model of the atmosphere used to calculate inlet conditions in the get_boundary_conditions.py script
    • 

      

      
  • 

    get_configuration_files.py: Configurable script that helps the user during the generation of large amounts of configuration files for each CFD simulation. For more information on the structure and the usage of these configuration files please visit the main repository: https://github.com/WyllDuck/OpenFOAM-ToolChain-for-Rocket-Aerodynamic-Analysis 
    • 




### CSV FILES



    

      
  • 

    CA_coefficients.csv: Axial Aerodynamic Coefficient vs. Angle of Attack and Mach Number
    • 

      

      
  • 

    CN_coefficients.csv: Normal Aerodynamic Coefficient vs. Angle of Attack and Mach Number
    • 

      

      
  • 

    Cm_coefficients.csv: Pitch Moment Aerodynamic Coefficient vs. Angle of Attack and Mach Number
    • 

      

      
  • 

    boundary_conditions.csv: All relevant inlet boundary conditions for each Mach number
    • 

      




## SOURCES



[1] J. C. Ferris. Static Stability Investigation of a Single-stage Sounding Rocket at Mach Numbers from 0.60 to 1.20. Tech. rep. 19670020050. Report/Patent Number: NASA-TN-D-4013, Accession Number: 67N29379. VA, United States: NASA Langley Research Center Hampton, July 1967. URL: https://ntrs.nasa.gov/citations/19670020050.



[2] C. D. Babb and D. E. Fuller. Static Stability Investigation of a Sounding-rocket Vehicle at Mach Numbers from 1.50 to 4.63. Tech. rep. 19670020031. Report/Patent Number: NASA-TN-D-4014, Accession Number: 67N29360. VA, United States: NASA Langley Research Center Hampton, June 1967. URL: https://ntrs.nasa.gov/citations/19670020031