Work out lift coefficient instantly with clear inputs, formula shown and shareable results.
Lift coefficient is the non-dimensional form of lift: CL = L / (q x S), where dynamic pressure q is half rho V squared. It tells you how hard the wing is working relative to its stalling capability, independent of speed and altitude.
Lift coefficient
CL = L / (0.5 x rho x V^2 x S)
Aviation results are planning estimates only. Always verify take-off, landing, fuel, weight and balance figures against the certified Aircraft Flight Manual, current performance charts and applicable aviation regulations before flight.
Around 0.2-0.5 for a fast aircraft in cruise, rising to 1.2-1.6 clean at the stall and 2.0-2.8 with full flaps and slats deployed.
Because it removes speed and density, letting a single wind-tunnel curve describe the wing at every condition.