AeroLab2D hybrid Navier–Stokes / panel-method airfoil laboratory

NACA 2412

α4.0°

V∞30 m/s

Re2.1×10⁶

Mach0.09

Portfolio

Forces & moments wind axes · per unit span

	LBM · NS	PANEL + BL
C_l	–	–
C_d	–	–
C_m,c/4	–	–
L/D	–	–
Lift [N/m]	–	–
Drag [N/m]	–	–

Force history LBM live · panel dashed

C_l C_d panel+BL steady value

Pressure distribution panel method · −C_p up

upper lower transition separation

Boundary layer Thwaites → Michel → Head

Freestream & scales

LBM solver internals