Parameter | Symbol | Unit | Value |
Wing area | Sref | m2 | 125.62 |
Mean aerodynamic chord | MAC | m | 4.388 |
Wing span | b | m | 34.546 |
Aspect ratio | Λ | - | 9.50 |
Taper ratio | λ | - | 0.17 |
Wing Section Parameters at η = y/c:
Parameter | Symbol | Unit | Values |
| η | - | 0.000 | 0.300 | 1.000 |
| y | m | 0.000 | 5.182 | 17.273 |
Chord length | c | m | 7.060 | 4.420 | 1.050 |
QC sweep angle | φ25 | ° | 20.91 | 23.74 |
LE sweep angle | φLE | ° | 27.00 | 27.00 |
TE sweep angle | φTE | ° | 0.00 | 13.00 |
Dihedral | ν | ° | 2.09 | 2.37 |
Twist angle | ε | ° | 0.00 | 0.00 | 0.00 |
Thickness ratio | t/c | % | 15.00 | 11.99 | 10.99 |
Airfoils | | | A1 | A2 | A3 |
Relative chord spar positions |
Front spar | x/c | % | 11.00 | 16.00 | 27.00 |
Rear spar | x/c | % | 55.00 | 65.00 | 55.00 |
Sweep angles and dihedral at spanwise stations η refer to the respective inner adjacent segment.
Fuel Tank Capacities:
1 Centre tank with 8215 kg.
2 Wing tanks with 11982 kg each.
Total fuel mass: 32179 kg.