Lift Coefficient Calculator
Invert lift to find C_L = 2L/(ρv²A).
Input Data
Input Lift L.
N
Input Fluid density ρ.
kg/m³
Input Velocity v.
m/s
Input Reference area A.
m²
Results
0.5
C_L = 2L/(ρv²A) = 0.500000
At a glance:Lift Coefficient Calculator: enter parameters to compute results; complements related calculators.
Formula
C_L = 2 L / (ρ v² A)
inverts L = ½ ρ v² A C_L
How to Use
- Enter lift L, density ρ, velocity v, area A.
- Get lift coefficient C_L.
Case Studies
L=15312.5 N at 50 m/s
ρ=1.225, A=20 → C_L=0.5.
FAQ
Typical C_L?
Cruise wing ≈0.3–0.5; takeoff flaps exceed 1.
Related Tools
References
Content review: Calculatorism Science Team. Formula and numeric tests verified; results for reference only.