Induced Drag Calculator

How to Use the Calculator

1. Enter the wing area in square meters (m²).
2. Enter the airspeed in meters per second (m/s).
3. Enter the air density in kilograms per cubic meter (kg/m³).
4. Enter the aspect ratio of the wing.
5. Click the "Calculate" button to compute the induced drag.
6. The result will be displayed in newtons (N).

Understanding Induced Drag

Induced drag is an aerodynamic force that occurs when an aircraft wing generates lift. It is a byproduct of lift and is proportional to the square of the airspeed and inversely proportional to the wing's aspect ratio. The formula used in this calculator is:

D_i = 0.5 * ρ * V² * (π * b² / (2 * A_r))

Where:

• D_i is the induced drag (N)
• ρ is the air density (kg/m³)
• V is the airspeed (m/s)
• b is the wing span (m)
• A_r is the aspect ratio

Example Calculation

For example, if an aircraft has a wing area of 30 m², an airspeed of 100 m/s, an air density of 1.225 kg/m³, and an aspect ratio of 8, the induced drag can be calculated as follows:

1. Wing span (b) = √(30 m² * 8) = 14.14 m
2. Induced drag (D_i) = 0.5 * 1.225 kg/m³ * (100 m/s)² * (π * 14.14 m² / (2 * 8)) = 343.14 N