The choice of taper ratio in aircraft wing design is a critical decision that affects the aerodynamic performance and structural characteristics of the wings. The taper ratio is defined as the ratio of the wing’s root chord (the chord length at the wing’s base) to its tip chord (the chord length at the wing’s tip).
Formula: The taper ratio (λ) is calculated using the following formula:
- λ is the taper ratio (dimensionless).
- Ct is the tip chord length (in meters, m).
- Cr is the root chord length (in meters, m).