---

Parameter	Symbol	Unit	Value
Wing area	Sref	m2	122.41
Mean aerodynamic chord	MAC	m	4.18
Wing span	b	m	34.07
Aspect ratio	Λ	-	9.48
Taper ratio	λ	-	0.24

Wing Section Parameters at η = y/c:

---

Parameter	Symbol	Unit	Values
	η	-	0.12	0.37	1.00
	y	m	2.00	6.37	17.04
QC sweep angle	φ25	°	0.00	20.74	24.54
LE sweep angle	φLE	°	0.00	27.00	27.00
TE sweep angle	φTE	°	0.00	-0.80	16.59
Dihedral	ν	°	0.00	5.00	5.00
Twist angle	ε	°	3.50	0.50	0.30
Thickness ratio	t/c	%	15.00	12.00	11.00
Airfoils			F15-15	F15-12	F15-11
Relative chord spar positions
Front spar	x/c	%	10.70	15.40	27.00
Rear spar	x/c	%	56.60	66.20	56.10

---

Sweep angles and dihedral at spanwise stations η refer to the respective inner adjacent segment.

Fuel Tank Capacities:

2 Wing tanks with 9339.2 kg each.

Max. fuel weight: 18678.3 kg.

Leading Edge Arrangement:

• 4 outboard slats from 0.13 (at η = 0.36) to 0.27 (at η = 0.96) local chord.
• 1 inboard slat from 0.09 (at η = 0.13) to 0.12 (at η = 0.32) local chord.

Trailing Edge Arrangement:

• 1 outboard aileron from 0.29 (at η = 0.79) to 0.25 (at η = 0.96) local chord.
• 1 outboard Fowler flap from 0.27 (at η = 0.37) to 0.28 (at η = 0.78) local chord.
• 1 inboard Fowler flap from 0.17 (at η = 0.12) to 0.27 (at η = 0.37) local chord.

Lift Distribution:

The data of lift distribution are available in a csv-file format: Lift Distr

The ​LIFTING_LINE output data file can be downloaded here (.xml): CalculatePolar LL
It includes full aircraft drag polars for different configurations and Mach numbers.

Wing Forces: