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sci.induced-drag-Oswald-efficiency Calculator
Calculates induced drag D_i = L²/(½ρv²π b² e) from lift and Oswald efficiency factor e, and the drag polar. Oswald efficiency e = 0.75–0.85 for real wings (elliptical planform gives e = 1) — induced drag dominates at low speed and decreases as v², so aircraft climb slowly to reduce it.
Inputs
W N
Body or object weight. For health calculators, usually in kg or lbs.
B M
Distance between supports (m). Longer spans experience larger bending moments — structural adequacy must be rechecked.
Rho Kgm3
Mass per unit volume (kg/m³). Water: 1,000. Air: 1.225. Steel: 7,850. Affects buoyancy, flow, and structural loads.
V Ms
Rate of movement. 1 m/s = 3.6 km/h = 2.237 mph.
E Oswald
Useful output divided by total input, as a percentage. 100% is impossible due to losses (heat, friction, resistance).
Results
induced drag Di (N)
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).
induced drag coefficient 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).
lift coefficient CL
Aerodynamic force perpendicular to the direction of motion. Lift = 0.5 × rho × v^2 × Cl × A. Enables flight when it exceeds weight.
aspect ratio AR = b²/S
The proportional relationship between two quantities.
CDi = CL²/(π·AR·e)
Reference formula or conversion factor shown for context.