Compute C_L and dynamic pressure from force, flow and geometry.
Results
Lift Coefficient (C_L)
0.1633
Dynamic Pressure (q)
1531.25 Pa
C_L = L / (0.5 × ρ × v² × A)
C_L is dimensionless. Dynamic pressure q = 0.5 ρ v².
Enter lift force (N), air density (kg/m³), velocity (m/s) and wing area (m²). The calculator returns C_L and q.
Lift 5000 N, ρ=1.225 kg/m³, v=50 m/s, A=20 m² → C_L ≈ 0.45 (example).
Q: Units? A: Use SI units. Q: Is C_L constant? A: It depends on angle of attack and flow.
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