🛩️ Lift & Drag Aerodynamic Simulation
🎮 Control Panel
Airfoil Profile
NACA 0012
NACA 2412
NACA 4412
Clark Y
Angle of Attack (α)
5°
Velocity (V)
50 m/s
Air Density (ρ)
1.225 kg/m³
Chord Length (c)
2.0 m
Wing Span (b)
10.0 m
Measurement Noise
2%
Calibration Mode
▶ Start Simulation
⏸ Stop
🔄 Reset
💾 Export CSV
📊 Real-Time Oscilloscope
Lift Force
0
N
Drag Force
0
N
Lift Coefficient
0
C
L
Drag Coefficient
0
C
D
L/D Ratio
0
-
Reynolds No.
0
×10⁵
Time Series
C
L
- C
D
Polar
Vector Field
Phasor Diagram
Pressure Map