诱导阻力计算器 — 公式
## Induced Drag
Induced drag is the aerodynamic penalty of generating lift. It arises because the wing creates trailing vortices that tilt the local flow downward, effectively rotating the lift vector backward.
### Formula
**CDi = CL² / (pi × e × AR)**
where CL is the lift coefficient, e is the Oswald span efficiency (typically 0.7 to 0.9), and AR is the aspect ratio. Induced drag dominates at low speeds and high CL, which is why it is critical during takeoff and climb.
Induced drag is the aerodynamic penalty of generating lift. It arises because the wing creates trailing vortices that tilt the local flow downward, effectively rotating the lift vector backward.
### Formula
**CDi = CL² / (pi × e × AR)**
where CL is the lift coefficient, e is the Oswald span efficiency (typically 0.7 to 0.9), and AR is the aspect ratio. Induced drag dominates at low speeds and high CL, which is why it is critical during takeoff and climb.
计算示例
A wing with CL=0.5, AR=10, e=0.85, at q=5000 Pa with S=100 m².
- CDi = 0.5² / (pi × 0.85 × 10)
- CDi = 0.25 / (26.704) = 0.00936
- Di = 0.00936 × 5000 × 100 = 4681 N