Finite Wing Induced Drag Calculator

Aerodynamic Drag Analysis: Calculate induced drag coefficient ($C_{Di}$), vortex drag force ($D_i$), and horsepower required ($P_i$) across speeds.

Aircraft Gross Mass $M$ (kg):

Airspeed $V_\infty$ (m/s):

Wingspan $b$ (m):

Wing Area $S$ (m²):

Planform Efficiency $e$:

Air Density $\rho_\infty$ (kg/m³):

Induced Drag Force ($D_i$)

-- N

Coeff C_Di: --

Induced Power Required ($P_i$)

-- kW

In Horsepower: -- hp

Lift-to-Induced Drag Ratio ($L/D_i$)

Current C_L: --

Span Loading ($W/b$)

-- N/m

Span Factor: b² = -- m²

Induced Drag Relationships:

• $D_i = \frac{2 L^2}{\pi \rho_\infty V_\infty^2 b^2 e}$: Vortex drag drops inversely with airspeed squared ($V^2$) and wingspan squared ($b^2$).

• At low takeoff or climb speeds, induced drag accounts for $60$–$80\%$ of total aircraft resistance.

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