Tools and methodologies for box-wing aircraft conceptual aerodynamic design and aeromechanic analysis

Advances of junior researchers in aerospace sciences: a focus on innovative design

Open Access

Table 3

Optimization constraints values.

Vertical trim
	with	• W_des	115000 kg
		• ϵ_L	2% of W_des
Longitudinal stability
	with	• SM_min	0.05
		• SM_max	0.3
Pitch trim
	with	• \|ϵ_M\|	0.1
Max local c_l
	with	•	0.7
Taper ratio
Relative wings position
	with	• Δx	0.5 m
Max wings loading
	with	(L_wing/S_wing)_max	case 1: 500 kg/m² case 2: 550 kg/m² case 3: 600 kg/m²

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