A modern, subsonic-supersonic, unstructured, aerodynamic panel code. We do linear aerodynamics for the twenty-first century.
A panel-based flow solver. Currently in beta but with working solvers for incompressible and inviscid hypersonic flow.
Discrete vortex panel method
Calculate common 2D airfoil parameters by just setting a few inputs and drawing the geometry of the body in a dynamic way
This project is prepared as part of CA course and it contains a study on the 2 dimensional Hess-Smith panel method (HSPM) for a cambered airfoil, NACA 1408.
A modern, unstructured, subsonic/supersonic flow solver.
High Performance CPU/GPU Potential Flow Solver
Hyunbin Kang's Portfolio
Efficient Foil Shape Optimization Using Artificial Neural Network-Based Surrogate Model with Adaptive Sampling Strategy
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