Lift Force Calculator
Compute lift L = ½ρv²AC_L.
Input Data
Input Fluid density ρ.
kg/m³
Input Velocity v.
m/s
Input Reference area A.
m²
Input Lift coefficient C_L.
Results
15,312.5N
L = ½ρv²AC_L = 15312.50 N
At a glance:Lift Force Calculator: enter parameters to compute results; complements related calculators.
Formula
L = ½ ρ v² A C_L
C_L: lift coefficient (from airfoil and angle of attack)
How to Use
- Enter fluid density ρ and velocity v.
- Enter reference area A and lift coefficient C_L.
- Get lift L.
Case Studies
Sea level, 50 m/s
ρ=1.225, v=50, A=20, C_L=0.5 → L≈15.3 kN.
FAQ
Where does C_L come from?
From airfoil geometry and angle of attack (wind-tunnel or polar data).
Related Tools
References
Content review: Calculatorism Science Team. Formula and numeric tests verified; results for reference only.