How to Calculate Induced Drag
Introduction & Importance
Induced drag is a crucial aspect of aerodynamics, affecting the performance of aircraft. Understanding and calculating it is vital for designing efficient aircraft.
How to Use This Calculator
- Enter the wing span, lift coefficient, and air density.
- Click ‘Calculate’.
- View the results and chart below.
Formula & Methodology
The induced drag coefficient (Cd_i) is calculated using the formula:
Cd_i = (2 * A * P) / (ρ * V^2 * S)
Where:
- A = Aspect ratio
- P = Lift coefficient (Cl)
- ρ = Air density
- V = Velocity
- S = Wing area
Real-World Examples
Data & Statistics
| Aircraft | Cd_i |
|---|---|
| Boeing 747 | 0.015 |
| Airbus A380 | 0.012 |
Expert Tips
- Increasing the aspect ratio reduces induced drag.
- High lift coefficients increase induced drag.
Interactive FAQ
What is the difference between induced and parasitic drag?
Induced drag is caused by the wings creating lift, while parasitic drag is due to skin friction and form drag.
For more information, see FAA’s Aircraft Handbook and NASA’s Airplane Design.