Report of wingDesign: CeRAS-CSR-02

Wing Planform Parameters:


ParameterSymbolUnitValue
Wing areaSrefm2125.62
Mean aerodynamic chordMACm4.388
Wing spanbm34.546
Aspect ratioΛ-9.50
Taper ratioλ-0.17

Wing Section Parameters at η = y/c:


ParameterSymbolUnitValues
η-0.0000.3001.000
ym0.0005.18217.273
Chord lengthcm7.0604.4201.050
QC sweep angleφ25°20.9123.74
LE sweep angleφLE°27.0027.00
TE sweep angleφTE°0.0013.00
Dihedralν°2.092.37
Twist angleε°0.000.000.00
Thickness ratiot/c%15.0011.9910.99
AirfoilsA1A2A3
Relative chord spar positions
Front sparx/c%11.0016.0027.00
Rear sparx/c%55.0065.0055.00

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.

Leading Edge Arrangement:

Trailing Edge Arrangement:

  • 1 inboard Fowler flap from 0.20 (at η = 0.12) to 0.30 (at η = 0.29) local chord.
  • 1 inboard (ground)spoiler from 0.12 (at η = 0.21) to 0.15 (at η = 0.29) local chord.
  • 1 outboard aileron from 0.30 (at η = 0.80) to 0.30 (at η = 0.98) local chord.
  • 1 outboard Fowler flap from 0.30 (at η = 0.31) to 0.30 (at η = 0.78) local chord.
  • 4 outboard (air)spoiler from 0.15 (at η = 0.31) to 0.15 (at η = 0.76) local chord.


  • All outputs of the program 'wingDesign' were created with version 2.0.0