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

Table 5

The results of using different thicknesses (invariably of core).

Mach no.	Skin thickness (mm)	Core thickness (mm)	Max deformation (mm)	Equivalent stress (MPa)	Equivalent strain (mm/mm)	Mass (kg)
0.4	2	2	149.83	208.83	0.00308	210.46
	2	4	138.66	203.51	0.002887	273.77
	2	6	129.37	196.4	0.002781	336.7
	3	2	104.24	141.84	0.002064	268.93
	3	4	98.149	136.93	0.001962	331.6
	3	6	93.145	130.62	0.001839	393.69
	4	2	80.478	113.23	0.001575	328.02
	4	4	76.558	104.97	0.001509	389.87
	4	6	73.405	100.77	0.001417	451.26
0.6	2	2	329.04	467.96	0.0069023	210.46
	2	4	304.44	456.06	0.0064775	273.77
	2	6	283.99	441.37	0.0065513	336.7
	3	2	228.96	321.24	0.0046238	268.93
	3	4	215.53	307.49	0.0044095	331.6
	3	6	204.5	294.99	0.004155	393.69
	4	2	176.79	260.86	0.003631	328.02
	4	4	168.13	237.86	0.003391	389.87
	4	6	161.18	227.4	0.003184	451.26
0.8	2	2	531.3	765.07	0.011286	210.46
	2	4	491.52	746.52	0.010595	273.77
	2	6	458.47	724.37	0.010264	336.7
	3	2	369.72	526.43	0.007557	268.93
	3	4	347.99	504.07	0.00723	331.6
	3	6	330.17	480.62	0.006771	393.69
	4	2	285.5	426.58	0.005938	328.02
	4	4	271.47	389.03	0.005558	389.87
	4	6	260.24	372.02	0.00522	451.26