International Journal of Aerospace Engineering / 2016 / Article / Tab 3

Research Article

Aeroelastic Analysis of Wings in the Transonic Regime: Planform’s Influence on the Dynamic Instability

Table 3

Structural analyses data.

Swept wingCurved wing

MaterialAluminium alloyAluminium alloy
Skin thickness7 mm to 2.5 mm7 mm to 2.5 mm
Rib thickness7 mm to 1 mm7 mm to 1 mm
Front spar thickness12 mm to 5 mm12 mm to 5 mm
Central spar thickness12 mm to 8 mm12 mm to 8 mm
Rear spar thickness12 mm to 7.5 mm12 mm to 7.5 mm
Total structural mass15 372.2 kg15 372.2 kg
Total fuel mass20 000 kg20 000 kg
Engine masses4000 kg front, 4000 kg centre, and 2000 kg rear4000 kg front, 4000 kg centre, and 2000 kg rear
Total model mass45 394 kg45 394 kg
Fictitious inertia (Case )1300, 1000, 10001300, 1000, 1000
Fictitious inertia (Case )750, 500, 5001050, 700, 700

Moment of inertia applied on ribs in the tip region ( direction): units = kg m2.