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

Table 1

Work plan.

Displacements and von Mises stresses
	1 cell									6 cells									9 cells
Mach no.	M = 0.4									M = 0.4									M = 0.4
Skin thickness (mm)	2			3			4			2			3			4			2			3			4
Core thickness (mm)	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6
Mach no.	M = 0.6									M = 0.6									M = 0.6
Skin thickness (mm)	2			3			4			2			3			4			2			3			4
Core thickness (mm)	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6
Mach no.	M = 0.8									M = 0.8									M = 0.8
Skin thickness (mm)	2			3			4			2			3			4			2			3			4
Core thickness (mm)	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6	2	4	6