Research Article
Transport Aircraft Conceptual Design Optimization Using Real Coded Genetic Algorithm
Table 2
Comparisons of the optimized values of decision variable.
| | Variable name | Developed model values | Chaudhry and Ahmed [9], calculated
values for Airbus A320-200 | Eurocontrol data base [31] |
| | Maximum takeoff weight (kg) | 72,511 | 74,439 | 73,900 | | Wing span (m) | 33.80 | 38 | 34.10 | | Wing aspect ratio | 9.45 | 10 | | | Wing reference area (m2) | 120.89 | — | | | Wing sweep angle (degree) | 25 | 25 | | | Horizontal tail span (m) | 12.07 | 15.30 | | | Horizontal tail area (m2) | 25.47 | — | | | Horizontal tail aspect ratio | 5.72 | — | | | Vertical tail span (m) | 6.01 | 6.12 | | | Vertical tail area (m2) | 19.47 | — | | | Vertical tail aspect ratio | 2.19 | — | | | Fuselage length (m) | 37.12 | 36.58 | 37.57 | | Fuselage diameter (m) | 3.75 | 4.572 | | | Engine thrust (KN) | 114.50 | — | 111–118 | | Range (Km) | 5,556 | 5330 | | | Specific fuel consumption (1/s) | 0.00019 | 0.00023 | | | Number of passengers | 192 | 195 | 180 | | Mach number | 0.785 | 0.79 | | | Cruise altitude (m) | 10,668 | 11229 | 12,497 | | Operating empty weight (kg) | 38,681 | — | | | Wing weight (kg) | 6,171 | | | | Fuselage weight (kg) | 7,773 | | | | Tail weight (kg) | 1,104 | | | | Propulsion system weight (kg) | 8,087 | | | | Undercarriage weight (kg) | 2,537 | | | | System group weight (kg) | 7,250 | | | | Surface controls weight (kg) | 848 | | | | Furnishing weight (kg) | 4,222 | | | | Contingency group weight (kg) | 725 | | | | Zero fuel weight (kg) | 54,414 | | | | Payload weight (kg) | 15,744 | | | | Fuel weight (kg) | 15,950 | | |
|
|
