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Inverse-Airfoil-Design

Project on Inverse Airfoil Design
Initial Airfoil which is to be modified is NACA0015 and target airfoil to be achieved is NACA0009.
Cp of the airfoils is plotted using XFOIL Software by Mark Drela MIT.
Project is Under Prof. A M Pradeep, Aeropsace Dept. IIT Bombay
Here is the Airfoil Generated
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Corresponding Cp Plots
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Corresponding Cp Plots
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Install Xfoil in Ubuntu 14.04

run sudo apt-get install xfoil in terminal

How to Run the code on Ubuntu 14.04

  1. Clone the repository
  2. Make sure that it has Modified.csv file is present
  3. Run linux_code.py
  4. Wait for the iterations to complete
  5. After iterations are completed Airfoils and Cp plots will automatically generate
  6. Important In order to run the code again delete Modified.csv, ModifiedCP.csv, n0009CP.csv and n0015CP.csv and put a new copy of Modified.csv now run the main code (Plots will be automatically replaced)

Ignore the Warning for replacing modified.csv as by default it automatically replaces it