Computational Aerodynamics Display & Evaluation System
Wind Tunnel VisualizerDrag Mouse to Inject Ink
LATTICE BOLTZMANN SOLVER
Chordwise Pressure Distribution-Cp vs Chord %
Live Telemetry
Lift Coeff (Cl)
0.00
Performance
00 FPS
Reynolds (Re)
150
Stall State
Normal
Wind Tunnel Configurations
Angle of Attack (AoA)0°
Viscosity / ReynoldsRe = 150
Inlet Velocity (u0)0.05
Background Field
Visual Overlay
Tunnel Design theme
Max Tracing Particles1200
Aerodynamic Context & Solver Physics
NACA 0012 Airfoil Profile: Calculated dynamically via half-thickness
y_t = 0.5946895√x - 0.126x - 0.3516x² + 0.2843x³ - 0.1015x⁴. Adjusting the Angle of Attack rotates the
solid boundary cells around the leading edge, regenerating the obstacle mask instantly.
Lattice Boltzmann Method (LBM D2Q9): Solving particle probability distributions
fi(x, t) on a structured lattice grid. Standard bounce-back boundary condition is
applied on the airfoil surface to achieve no-slip. Zou-He velocity boundaries drive the flow at the inlet (left),
while zero-gradient convective extrapolation stabilizes the exit (right). A local Smagorinsky Subgrid Scale LES Model
is active to stabilize wake shedding and prevent numerical blowups (NaN instabilities) at high Reynolds numbers.