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 | ā | 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 = 57275ā(kg) |
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