Aerodynamic Lift Force of Airfoil Calculator
Editable data
constant of proportionality k1 = -
angle of attack α =  deg
negative of angle of attack β = deg
Air Density ρ = kg/m3
fluid velocity V = m/s
Projected area of airfoil Ap = m2
Calculator Results
Approximate Lift coefficient CL = -
Lift force FL = N
 
Aerodynamic Lift Force of Airfoil Calculator
Air Density ρ = kg/m3
fluid velocity V = m/s
Projected area of airfoil Ap = m2
Known Lift coefficient CL = -
Calculator Results
Lift force FL = N
 
Airfoil Drag Coefficient
 span length b = m
plan area Ap = m2
Lift coefficient CL = -
infinite span drag coefficient CD∞ = -
Calculator Results
aspect ratio AR = -
Approximated drag coefficient CD = -