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

Table 3

Wing one cell at angle of attack 12° (6 cells).

Mach no.	Skin thickness (mm)	Core thickness (mm)	Max deformation (mm)	von Mises stress (MPa)	Equivalent strain (mm/mm)	Mass (kg)
0.4	2	2	154.28	210.17	0.003177	200.2
	2	4	146.39	217.08	0.003156	253.5
	2	6	138.16	195.19	0.002785	306.6
	3	2	106.41	143.64	0.00204	258.8
	3	4	101.88	140.54	0.002052	311.5
	3	6	98.262	137.65	0.001964	363.8
	4	2	81.681	110.74	0.001557	318
	4	4	78.785	108.41	0.001577	370
	4	6	76.48	104.37	0.001484	421.7
0.6	2	2	338.84	473.87	0.00715	200.2
	2	4	321.44	487.8	0.00709	253.5
	2	6	308.4	515.52	0.007238	306.6
	3	2	233.76	324.6	0.00461	258.8
	3	4	223.74	316	0.00462	311.5
	3	6	215.75	309.67	0.00442	363.8
	4	2	179.45	253.16	0.00353	318
	4	4	173.04	244.05	0.00355	370
	4	6	167.95	235.52	0.00334	421.7
0.8	2	2	547.06	774.53	0.011689	200.21
	2	4	518.87	793.92	0.011543	253.46
	2	6	489.42	718.16	0.010246	306.56
	3	2	377.45	530.72	0.007541	258.8
	3	4	361.19	514.4	0.007548	311.5
	3	6	348.26	503.78	0.007197	363.82
	4	2	289.77	413.8	0.005768	317.96
	4	4	279.36	398.98	0.005801	369.96
	4	6	271.12	358.11	0.005433	421.71