|
| Parameters | Specifications | Parameters | Constant values |
|
| Wing configuration | Low wing | Tail arm moment, lht,m | 0.55 of Lf |
| Wing planform | Backward sweep | Wing sweep angle, ΛC/4, (°) | 29 |
| Root section airfoil | NASA SC 0412 | Ultimate load factor, Nult | 6 |
| Tip section airfoil | NASA SC 0410 | Maximum thickness-to-chord ratio, (t/c)max () | 0.12 |
| t/c location of root chord, kR | 0.37 | Density of wing material, , kg/m3 | 2106 |
| t/c location of tip chord, kT | 0.38 | | 0.0025 |
| Dihedral angle | 2.3° | Density of fuselage material, ρmat,f, kg/m3 | 2682.3 |
| Fuselage configuration | Twin aisle | Fuselage density factor, Kρf | 0.0025 |
| Tail configuration | Conventional | HT sweep angle, ΛC/4,HT,° | 34 |
| Root section airfoil | NASA 0009 | Elevator-to-tail chord ratio, Ce/CT | 0.35 |
| Tip section airfoil | NASA 0009 | Maximum thickness-to-chord ratio, (t/c)maxHT | 0.09 |
| Tip section airfoil | NASA (LS) 0410 | Density of HT material, ρmat,HT, kg/m3 | 2106 |
| VT sweep angle, ΛC/4,HT,° | 44 | HT density factor, KρHT | 0.02 |
| Elevator-to-tail chord ratio, Cr/CT | 0.25 | Retractable landing gear factor, Kret | 1.07 |
| Landing gear configuration | Multibogey | LG density factor, KLG | 0.32 |
| LG tires | 2; 8 | Landing gear height, HLG | 0.5 |
| Aircraft paint coefficient | 6.45 10−6 | Engine weight factor, KE | 3 |
| Oswald efficiency | 0.8 | Number of engines installed, NE | 2 |
|
| Design variables | Notations | Baseline | Generic value | Optimized value |
| Lower bound | Upper bound |
|
| Wing area (m2) | | 219 | 122 | 845 | 200.0 |
| Wing span (m) | | 43.9 | 33.9 | 79.8 | 42.87 |
| Taper ratio of wing | | 0.259 | 0.2 | 0.35 | 0.32 |
| Length of the fuselage (m) | Lf | 46.70 | 33.8 | 76.73 | 47.2 |
| Diameter of the fuselage (m) | Df | 5.7 | 4 | 6.2 | 5.9 |
| Horizontal tail surface area (m2) | SHT | 76.8285 | 63 | 81.5 | 69.1 |
| Horizontal tail span length (m) | bHT | 16.26 | 12.45 | 31.29 | 16 |
| Taper ratio of horizontal tail | λHT | 0.34 | 0.25 | 0.38 | 0.385 |
| Vertical tail surface area (m2) | SVT | 45.235 | 30.5 | 45.5 | 52.2 |
| Vertical tail span length (m) | bVT | 8.3 | 7.5 | 9.5 | 7.97 |
| Taper ratio of vertical tail | λVT | 0.39 | 0.30 | 0.32 | 0.31 |
| Aerodynamic efficiency | L/D | 16.3 | 15 | 18 | 16.7 |
| Design objective (N) | MTOW | 14,12,640 | — | — | 13,59,690 |
|
