Aerodynamic Optimization Lab

Interpreting the mathematical laws of flight

Optimization Mission

FIND MAX LIFT

🎯

Control Systems

0°
-10° 0° 15° (CRITICAL) 30°

Step 1: Calculating $C_L$

Thin Airfoil Theory

$$ C_L = a_0 \cdot (\alpha - \alpha_0) $$
$a_0$ (Lift Slope) 0.11 / deg
$\alpha_0$ (Zero-Lift Angle) -2.0°
Resulting $C_L$ 0.00

Step 2: Total Lift Force

$$ \class{math-l}{L} = \frac{1}{2} \rho v^2 S \class{math-cl}{C_L} $$
$\rho$ (Air Density) 1.225 kg/m³
$v$ (Velocity) 50.0 m/s
$S$ (Wing Area) 20 m²
$C_L$ (coefficient) 0.00

Lift Force Output

($L$)

0 N

Virtual Wind Tunnel Laminar

Aerodynamic Performance

$C_L$
Lift Force ($N$)