The lift and drag coefficients are the dimensionless number that describes the lift and drag forces generated by an object relative to the dynamic pressure and the reference area.
Lift Coefficient (CL) Calculator
Lift Coefficient (CL) will appear here
Drag Coefficient (CD) Calculator
Drag Coefficient (CD) will appear here
Pitching Moment Coefficient (Cm) Calculator
Pitching Moment Coefficient (Cm) will appear here
Lift =1/2⋅CL⋅ρ⋅A⋅U²
Drag =1/2⋅CD⋅ρ⋅A⋅U²
Moment = 1/2 . Cm.ρ⋅A⋅U².c
Where:
L = Lift (N)
D = Drag (N)
CL = Lift coefficient
CD = Drag coefficient
ρ = density (kg/m³)
A = Reference Area (m²)
U = magnitude of velocity (m/s)
The value of the reference area depends on your own conversions, and must be consistent with previous works. For example, aircraft wings usually use span*chord, truck aerodyamics use frontal area, or submarine hydrodynamics use wetted surface.