Airfoil & Flowfield Visualizer

CL vs α Polar Linear Range

Drag on canvas to pitch airfoil (α) • Scroll to zoom

Flight Presets

NACA 4-Digit Profile

NACA

Max Camber (m) 2 %

Camber Position (p) 40 %

Max Thickness (t) 12 %

High-Lift Devices

Flap Deflection (δ_f) 0°

Leading-Edge Slat

Flight Conditions

Angle of Attack (α) 5.0°

Airspeed (V_∞) 60 m/s

Air Density (ρ) 1.225 kg/m³

Visual Overlays

Aero Vectors (L, D, R) Camber Line Chord & CP Marker Wake Vortex Shedding

Aerodynamic Balance

Lift Force (L) 2,160 N

Drag Force (D) 47.4 N

Dynamic Pressure (q) 2,205 Pa

Pitching Moment (Cm) -0.050