Aeroplane Wing Lift Simulation
Wing Parameters
Value: 2.5 m²
Value: 1.3 kg/m³
Airflow Velocities
Value: 70 m/s
Value: 63 m/s
Results
Pressure Difference (ΔP): 0 Pa
Lift Force: 0 N
Bernoulli's Principle
P₁ + ½ρv₁² = P₂ + ½ρv₂²
ΔP = P₂ - P₁ = ½ρ(v₁² - v₂²)
Lift = ΔP × A = ½ρ(v₁² - v₂²) × A
