Table 4.
Aircraft design and performance data for the three scenarios (sized for design mission range of 2940 nmi)
| Baseline | Sequential | Simultaneous | |
|---|---|---|---|
| Design variables | |||
| Aspect ratio | 9.4 | 11.99 | 8.32 |
| Taper ratio | 0.159 | 0.1 | 0.158 |
| Thickness-to-chord ratio | 0.1338 | 0.091 | 0.1338 |
| Wing area [sq.ft] | 1345.5 | 1343.3 | 1309.8 |
| Sweep [deg] | 25.0 | 13.98 | 24.98 |
| Thrust per engine [lbs] | 24200 | 24200 | 24172.3 |
| Performance data | |||
| Gross weight [lbs.] | 169,028 | 163,612 | 170,099 |
| Total operating cost [$] | 67,418 | 66,449 | 67,533 |
| Empty weight [lbs.] | 79,593 | 83,272 | 87,043 |
| Fuel burn [lbs.] | 46,967 | 37,884 | 49,197 |
| Thrust-to-weight ratio | 0.286 | 0.296 | 0.284 |
| Wing loading [lbs./sq.ft.] | 125.6 | 121.8 | 129.9 |