Analyze Airfoil Performance with Vortex Panel Method

This app uses a vortex panel method to compute the inviscid, incompressible flow around NACA 4-digit airfoils. Whether you're a student, engineer, or aviation enthusiast, it offers a fast and flexible way to study aerodynamic behavior.

✈️ Key Features:
Solve for flow around NACA 4-digit series airfoils
Choose between open or closed trailing edges
Customize angle of attack and number of panels (nodes)
View detailed pressure distribution plots
Visualize flow streamlines and circulation patterns
Calculate key coefficients:
Lift coefficient (CL)
Moment coefficients (CM)
Circulation (Γ)
?️ Built for Aerodynamics Enthusiasts:
Ideal for aerospace students, CFD beginners, or anyone exploring classic panel methods without the complexity of full CFD solvers.