基于pyfluent的全流程应用案例（以2D naca0012为例）

ANN based Surrogate model optimization of airfoil using XFOIL

A Python-based 2D CFD solver for the Euler equations using a structured O-type grid. Capable of simulating flow around airfoils in subsonic, transonic, and supersonic regimes.

Naca 0012 pimpleFoam simulation comparison with experimental results

Dynamic-stall prediction on a helicopter retreating blade (NACA 0012) using UNISTALL — a reduced-order Unified Indicial–Beddoes State-Space (UIBS) solver — validated against NASA static and dynamic-stall experiments. Full geometry→mesh→solve→validate pipeline with plots, drawings, and technical report.

Aerospace CFD verification workflow using OpenFOAM for NACA 0012 airfoil analysis, mesh refinement and CL/CD convergence assessment.

aerodynamic simulation of the NACA 0012

2D CFD simulation of NACA0012 at 5° AoA using SST k-ω model. Mesh convergence included.