WIND TUNNEL SIMULATOR
Select an airfoil profile to begin aerodynamic testing
WING SPECS
Chord:
0.30 m
Span:
1.50 m
Area:
0.45 m²
Air density:
1.225 kg/m³
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NACA 0012
LIVE TEST
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Test All Airfoils
Lift Force
0.00
Newtons (N)
Aerodynamic Lift
⚠ STALL DETECTED
Aerodynamic Forces
0.00
Drag (N)
—
L/D Ratio
0.000
Cl
0.000
Cd
Flow Parameters
Dynamic Pressure
— Pa
Reynolds Number
—
Flow Regime
—
Flow Visualization
Fast / Low Pressure
Slow / High Pressure
Wind Speed
30 m/s
Angle of Attack
5°
AIRFOIL COMPARISON
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Airfoil
Cl
Lift (N)
Drag (N)
L/D Ratio
Max Cl
Peak AoA
Stall AoA