// multi-utility computation suite · offline · instant · precise
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eng.aerodynamic-drag-polar Calculator
Calculates the aerodynamic drag polar (CL vs. CD) and lift-to-drag ratio from parasite drag and induced drag coefficients. Maximum L/D occurs at the speed where induced drag equals parasite drag — gliders achieve L/D of 40–70; commercial aircraft 16–20.
Inputs
Cl
Reference formula or conversion factor shown for context.
Cd0
Reference formula or conversion factor shown for context.
Ar
Reference formula or conversion factor shown for context.
E
Useful output divided by total input, as a percentage. 100% is impossible due to losses (heat, friction, resistance).
Q Pa
Force per unit area (Pa). Atmospheric pressure at sea level: 101,325 Pa. Check whether gauge or absolute pressure is required.
S M2
Two-dimensional surface extent (m²). For complex shapes, break into simpler sub-shapes and sum.
Results
induced drag CDi
Aerodynamic resistance opposing motion. Drag = 0.5 × rho × v^2 × Cd × A. Doubles with every 41% increase in speed (because it scales with v^2).
total drag coefficient CD
The combined total across all inputs and components.
lift-to-drag ratio L/D
The proportional relationship between two quantities.
lift L (kN)
Aerodynamic force perpendicular to the direction of motion. Lift = 0.5 × rho × v^2 × Cl × A. Enables flight when it exceeds weight.
drag D (kN)
Aerodynamic resistance opposing motion. Drag = 0.5 × rho × v^2 × Cd × A. Doubles with every 41% increase in speed (because it scales with v^2).
CD = CD₀ + CL²/(π·AR·e)
Reference formula or conversion factor shown for context.