Airfoil Analysis

XFOIL-style lift, drag and pressure distribution for a section.

Web XFOIL (React + Recharts)Analytic airfoil demo with NACA library, section polars, and Cp distribution. Swap the analytic model out for a real XFOIL WebAssembly backend to turn this into a full solver front-end.
Airfoil & Flow
Airfoil library
NACA 4-digit
Reynolds (Re)
Mach
Alpha sweep
alpha start [deg]
alpha end [deg]
delta alpha [deg]
Cp slice
alpha for Cp(x) [deg]
Airfoil geometry
NACA 2412 | chord c = 1.0
Section polar (demo)
Cp distribution (demo)
Cp(x) at alpha = 4 deg(simple analytic slice)
Hit Run to generate demo geometry and polars. To turn this into a full XFOIL front-end, plug in your WebAssembly-compiled XFOIL core and replace the analytic generators with its outputs.

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Web XFOIL (React + Recharts)Analytic airfoil demo with NACA library, section polars, and Cp distribution. Swap the analytic model out for a real XFOIL WebAssembly backend to turn this into a full solver front-end.
Airfoil & Flow
Airfoil library
NACA 4-digit
Reynolds (Re)
Mach
Alpha sweep
alpha start [deg]
alpha end [deg]
delta alpha [deg]
Cp slice
alpha for Cp(x) [deg]
Airfoil geometry
NACA 2412 | chord c = 1.0
Section polar (demo)
Cp distribution (demo)
Cp(x) at alpha = 4 deg(simple analytic slice)
Hit Run to generate demo geometry and polars. To turn this into a full XFOIL front-end, plug in your WebAssembly-compiled XFOIL core and replace the analytic generators with its outputs.