Research Article
Transport Aircraft Conceptual Design Optimization Using Real Coded Genetic Algorithm
Table 1
Design variables and their limits and constants.
| | Design variable | Limits |
| | Wing span (m) | | | Wing reference area (m2) | | | Wing sweep angle (degree) | | | Fuselage length (m) | | | Fuselage diameter (m) | | | Horizontal tail area (m2) | | | Vertical tail area (m2) | | | Specific fuel consumption (1/s) | | | Engine thrust (KN) | 110 < Th < 120 | | Constant values | | | Ultimate load factor | | | Average wing thickness ratio | | | Wing root chord (m) | cwr = 6.08 | | Maximum design speed (m/s) | | | Number of engines | | | Engine dry weight (kg) | | | Fudge factor for the wing | | | Fudge factor for the fuselage | | | Fudge factor for tail | | | Fudge factor for the nacelle | | | Aircraft range (NM) | | | Mach number | Mcruise = 0.785 | | Lift/drag ratio | (L/D) max = 18.5 | | Cruise altitude (ft) | Alt = 34961 to 38961 | | Maximum zero fuel weight (kg) | Mzf = 57275 (kg) |
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