Post-Processing Airfoil CFD simulation in OpenFOAM | Python & ParaView (Part 1) скачать в хорошем качестве

Post-Processing Airfoil CFD simulation in OpenFOAM | Python & ParaView (Part 1)

📂 Download Project Files (Case + Data): 👉 https://ahmedfreelance.gumroad.com/l/... 🔗 Previous Video (Setup & Simulation): 👉    • Auto 2D Airfoil CFD | Multi AoA | Python +...   Welcome back to Automated Engineering Solutions | AutoES | 👨‍💻 In this video (Part 1 of the Post-Processing Series), we explore how to analyze CFD results in OpenFOAM using Python and ParaView. 📁 Topics covered: Exploring the postProcessing folder structure Understanding forces.dat Reading pressure sample data on the airfoil surface Preparing data for lift and drag coefficient calculations 🧩 Video Steps Summary (Part 1 Script Recap) 1- Define Monitored Variables: Before running the simulation, specify all variables you need to monitor and extract during and after the run. 2- Edit controlDict: Go to your project folder → system → open controlDict. Scroll to the end of the file and add the functions section. The first function extracts forces and moments on the airfoil patch (ensure the patch name matches your boundary file). 3- Add Pressure Sampling Function: The second function samples pressure values on the upper and lower surfaces of the wing every 100 time steps. This will allow you to later plot the pressure coefficient (Cp) distribution. 4- Run the Simulation: Save the modified controlDict. Open the terminal, navigate to your project folder, and run the simulation using: simpleFoam 5- Check Results: After the run completes, observe the force convergence and final lift/drag values in the terminal output. 6- Explore the Post-Processing Folder: A new folder named postProcessing will be created automatically. Inside, you’ll find: forces/ → contains forces.dat and moment.dat with pressure and viscous components. samplePressure/ → includes raw pressure data (coordinates and pressure values). 7- Next Step (Part 2 Preview): We’ll visualize these results in ParaView to create qualitative and quantitative plots for the airfoil.