An Analytical-Based Lightning-Induced Damage Model for an Aircraft Wing Exposed to Pressure Loading of Lightning

Table 11

Amount of torsion deflection in an aircraft wing at different locations (x₀) with respect to damping coefficient (ξ).

Torsion deflections at lightning strike point in Zone 2A (mm) (ξ vs x0)
Zone 2A (ξ/x0)	Wing root (x0 = 0.5 m)	Mid-wing (x0 = 3.0 m)	Wing tip (x0 = 4.5 m)
ξ = 0	0.8884	1.9895	2.3523
ξ = 0.0050	0.8875	1.9883	2.3497
ξ = 0.01	0.8866	1.9871	2.3471
ξ = 0.0150	0.8858	1.9859	2.3445
ξ = 0.02	0.8849	1.9848	2.3422