An Optimum Design of a Subsonic Aircraft Wing due to the Aerodynamic Loading

Table 6

Comparison between the current work and that reported by Gargan [29].

Current work
Skin thickness (mm)	Core thickness (mm)	Max deformation (mm)	von Mises stress (MPa)	Stress ratio	Mass (kg)
2	2	338.84	473.87	1.066	200.21
2	4	321.44	487.8	1.035	253.46
2	6	308.4	515.52	0.979	306.56
3	2	233.76	324.6	1.556	258.8
3	4	223.74	316	1.598	311.5
3	6	215.75	309.67	1.631	363.82
4	2	179.45	253.16	1.995	317.96
4	4	173.04	244.05	2.064	369.96
4	6	167.95	235.52	2.144	421.71
Mr. Gargan [29]
Skin thickness (mm)	Displacement (m)	von Mises stress (MPa)		Mass (kg)
15	0.056	460		414
2	0.047	361		440
25	0.041	298		467
3	0.037	254		493
3.5	0.032	221		520