Research Article
Tradeoff Study between Cost and Environmental Impact of Aircraft Using Simultaneous Optimization of Airframe and Engine Cycle
Table 5
Results of single objective optimization cases.
| | Parameter | Baseline | Design A
min DOC | Design B
min | Design C
min | Design D
min |
| | Wing reference area (m2) | 355.49 | 332.02 | 389.71 | 400.00 | 312.72 | | Wing sweep (°) | 32.4 | 30.46 | 29.40 | 32.88 | 28.49 | | Wing aspect ratio | 10.4672 | 12.88 | 12.94 | 13 | 12.70 | | Wing taper ratio | 0.1062 | 0.1130 | 0.1128 | 0.1004 | 0.1116 | | Ratio of thickness to chord at root | 0.135 | 0.1132 | 0.1121 | 0.1374 | 0.1117 | | Engine takeoff thrust (kN) | 334 | 307.91 | 390.84 | 293.03 | 419.38 | | Bypass ratio | 11 | 10.70 | 13.06 | 10.25 | 8.121 | | Fan pressure ratio | 1.58 | 1.658 | 1.554 | 1.649 | 1.699 | | LPC pressure ratio | 3.2 | 4.419 | 3.768 | 2.954 | 4.418 | | Overall pressure ratio | 52 | 53.78 | 56.82 | 40.06 | 40.65 | | Turbine inlet temperature (K) | 1800 | 1794.1 | 1787.2 | 1708.6 | 1677.7 |
| | Takeoff field length (m) | 2714.8 | 2670.7 | 2233.1 | 2585.4 | 2317.5 | | Landing field length (m) | 1690.8 | 1666.1 | 1582.6 | 1537.4 | 1762.2 | | Engine-out climb gradient | 0.0253 | 0.0302 | 0.0441 | 0.0241 | 0.0623 | | Rate of climb at TOC (m/s) | 2.8413 | 3.035 | 3.250 | 1.622 | 8.562 |
| | Maximum takeoff weight (kg) | 230870 | 220875 | 239816 | 231857 | 227799 | | Block fuel consumption | 69661 | 62382 | 66195 | 66708 | 67431 |
| | DOC (RMB/PAX/km) | 0.31351 | 0.29560 | 0.33446 | 0.30207 | 0.32310 | | (EPLNdB) | 278.3 | 279.3 | 268.9 | 275.9 | 273.2 | | (kg) | 7.500 | 7.241 | 9.174 | 4.383 | 6.892 | | (kg) | 615.1 | 637.9 | 699.3 | 493.1 | 241.1 |
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