Modelling and Design Optimization of a Novel Wide-Body Transport Aircraft to Improve the Structural Integrity

Table 8

Constraint requirements as per airworthiness.

Requirements		Formulation	Limits	Reference
Retrofit design	Wing aspect ratio	= b^2/S	9.9 <  < 6.9	[22]
	Wing root chord		9.1 <  < 6.9	[22]
	Fuselage fineness ratio		12.3 < FR < 8.2	[12, 22]
	Horizontal tail aspect ratio	ARHT = bHT^2/SHT	3 < ARHT < 5	[22]
	Horizontal tail root chord	CR,HT =	8 < CR,HT < 4	[22]
	Vertical tail aspect ratio	ARVT = bVT^2/SVT	1.3 < ARVT < 2.0	[22]
	Vertical tail root chord	CR,HT =	8 < CR,VT < 5	[22]
Operational performance	Flight take-off distance		1400 < STO < 2550	[12, 20]
	Rate of climb		5.08 < ROC < 28.9	[12, 20]
	Volume of fuel tank		62 <  < 85	[12]
Static stability characteristics	Tail volume coefficient		= 1	[32]
	Fin volume coefficient		= 0.07	[32]
	Static margin		0.05 <  < 0.1	[20, 22, 23]
	Longitudinal dynamic stability	Phugoid damping ratio,	ζph > 0.04 or 0	[23]