BIRRUNG
INNOVATIVE FEATURES
Modern flight control for easy flight
Cutting edge avionics systems for reduced pilot stress
All weather radar allowing for operation under any conditions
Larger windows and seats with extra leg room for better passenger comfort
TWO CFM56-5C ENGINES MODIFIED
Exceptional environmental performance
Easy maintenance
OVERVIEW
250 PAX + 7 Crew
Max Range: 9000 km
Cruise Speed at Mach 0.8
Cruising altitude of 36 000 ft
19% better fuel economy over competitors*
AERODYNAMIC
Advanced aerofoil with leading edge slats and double slotted flaps
Raked wingtips for improved fuel efficiency
Contoured engine pylon
STRUCTURE & MATERIALS
Modern and advanced materials for reduced weight
Advanced metal and ceramics for engines
Titanium landing gear
01
02
ALL DIMENSIONS ARE STATED IN METERS AND DEGREES
ALL DIMENSIONS STATED ARE IN METERS AND DEGREES
02
AERODYNAMICS
L/D
20.7
Cruise Mach
0.8
W/S
5 240 Pa
Cruise CL
0.4
Aspect Ratio
9.66
Engine Mass
ENGINE CFM56-5C MODIFIED
2644.4 kg
Engine Length
2.62 m
Fan Diameter
1.84 m
Bypass Ratio
6.5 : 1
Maximum Thrust
151.24 kN
TSFC
10.49 g/kN.s
Cruise Thrust
40.14 kN
MTOW
WEIGHTS (kg)
98 246
27 500
26 843
Structural Mass
43 903
23 675
Payload at 7 000 km
Fuel Mass at 7 000 km
Payload at 9 000 km
30 637
Fuel Mass at 9 000 km
Thrust : Weight
0.31
WING
L.E. Device Flapped Area
58.67 m^2
T.E. Device Flapped Area
70.40 m^2
Take-off Flap Deflection
19%
Landing Flap Deflection
32%
Reference Area
176 m^2
Aileron Deflection Angle
[-20° : 20°] ± 0.5°
TAIL
VERTICAL
HORIZONTAL
Volume Coefficient
0.08878
Flapped area (m^2)
35.73
Control Surface Deflection Angle
[-22° : 22°] ± 0.5°
Reference Area (m^2)
1.0569
20.44
29.19
[-24.5° : 24.5°]± 0.5°
43.57
Specifications
Direct
Operating Cost
ALL VALUES ESTIMATED IN AUD
04
BIRRUNG
9 515.17
7 248
5 617.20
Maintenance
7 112.1
29 492
Crew
Insurance + owners
Total DOC
Fuel
10 859.93
9 320
7 223
9 145.25
36 548.18
1 050.24
800
620
785
3255.24
932.18
800
620
785
3 137.18
7 000 km
9 000 km
Per hr. at
7 000 km
Per hr. at
9 000 km
A321 XLR
11 645.62
7 153.44
5 543.92
Maintenance
7 019.31
31 362.28
Crew
Insurance + owners
Total DOC
Fuel
12 908.98
9 210.58
7 138.20
9 037.88
38 295.65
1 302.38
800
620
785
3 507.38
1 121.23
800
620
785
3 326.23
6 760 km
8 704 km
Per hr. at
7 000 km
Per hr. at
9 000 km
05
Emissions Reductions
MODIFIED
CFM56-5C ENGINES
EXCEPTIONAL ENVIORNMENTAL PERFORMANCE
Reduced NOx emissions
DESIGNED FOR MAINTENANCE
99.9% dispatch reliability rate
0.03 shop visit rate
NOISE REDUCTION
TECH INSERTION PROGRAM
Focuses on engine efficiency and longetivity
05
Emissions Reductions
MODIFIED
CFM56-5C ENGINES
EXCEPTIONAL ENVIORNMENTAL PERFORMANCE
Reduced NOx emissions
DESIGNED FOR MAINTENANCE
99.9% dispatch reliability rate
0.03 shop visit rate
NOISE REDUCTION
TECH INSERTION PROGRAM
Focuses on engine efficiency and longetivity
Constraint Analysis
WING LOADING
5240 Pa
THRUST LOADING
0.2365
OPTIMAL DESIGN PARAMETERS
Design envelope bounded by Cruise Climb, JAR-25 and Landing Constraints
07
FOLDABLE RAKED WINGTIP
CL W/OUT HIGH LIFT SYSTEM
0.4874
1.566
1.097
CL W/ HIGH
LIFT SYSTEM
0.4874
3
2.5
CRUISE
LANDING
TAKEOFF
W/OUT HLD
FULLY EXTENDED
FULLY EXTENDED
AoA (Degrees)
3.521
14.13
11.20
HIGH LIFT DEVICES
LEADING EDGE
TRAILING EDGE
Aerodynamics
NACA 64(1) - 212 MOD B
Area
7.42 m^2
Sweep Angle
55°
Span of 2 Wingtip
2.395 m
Moulding
2°
MASS PARAMETERS (kg)
Fuselage
7 691
Wing Structure
7 944
Tail Structure
1 668
Engines, Pylons, etc
8 251
Internals
13 754
Operational Items
4 595
Fuel at 7000 km
26 843
Payload at 7000 km
8 27 500
Empty Mass
43 903
MTOW
98 246
08
Mass estimations calculated through Howe estimates
Internals inclusive of seats, galleys, systems etc
Operational items inclusive of water, food, etc
FUEL DISTRIBUTION
Two wing tanks
Maximum volume: 41 080 L
Centre tank option available for 9 000 km range
COMPOSITE SELECTION
Composites used for weight reduction in main body
FUSELAGE
70:30 Al/CF (by wt.)
WING
75:25 Al/CF (by wt.)
Weight Breakdown
Gear Height
2.06
Nose Landing Gear Position
5.94
Main Landing Gear Position
25.4
Main Gear Tyre Radius
0.876
Main Gear Tyre Width
0.248
Nose Gear Tyre Radius
0.711
Nose Gear Tyre Width
0.229
Wheel Track
7.17
DIMENSIONS (m)
Landing Gear
KEY FEATURES
All struts equipped with oleo shock absorbers
Multi-disk brakes & anti-skid tyres
Constructed of Titanium alloys
12° angle of clearance
2° tip-over angle and 44° over-turn angle
MAIN
4 Wheels
90% of load carried
NOSE
2 Wheels
10% of load carried
RETRACTABLE TRICYCLE LANDING GEAR
09
ECONOMY CLASS
BUSINESS
Lavatory - 5
Galley - 3
Emergency Exit -10
Cabin Interiors
PRIME CUSTOMER EXPERIENCE
Lengthened seat pitch in comparison to A321 XLR for added customer comfort, with slimmer seat designs to boast a more spacious flight environment.
ECONOMY
Seat Pitch 30.5"
BUSINESS
Seat Pitch 36"
3.7 m
3.5 m
0.44 m
0.48 m
4.259 m
4.159 m
2.15 m
1.62 m
250 PAX .
MAX RANGE OF 9 000 KM .
LOWER GREENHOUSE EMISSIONS .
19% IMPROVED FUEL EFFICIENCY .
CUTTING EDGE TECHNOLOGY .
BIRRUNG .
250 PAX .
MAX RANGE OF 9 000 KM .
LOWER GREENHOUSE EMISSIONS .
19% IMPROVED FUEL EFFICIENCY .
CUTTING EDGE TECHNOLOGY .
BIRRUNG .
APPENDIX A
TWIST DISTRIBUTION & AEROFOIL THICKNESS
APPENDIX B
LIFT TO DRAG RATIO
APPENDIX C
PARASITIC DRAG ESTIMATED USING OPENVSP
Boundary layer approximated by turbulent Prandtl high-Re correlations
Friction factors summed up in proportion to yield Cd0
DRAG POLAR
LIFT MODEL USED
APPENDIX D
THRUST
TWO-ENGINE JET AIRCRAFT
APPENDIX E
ENLARGED CONSTRAINT PLOTS
REFERENCES
[1] i. effects et al., "US5381986A - Folding wing-tip system - Google Patents", Patents.google.com, 2020. [Online]. Available: https://patents.google.com/patent/US5381986A/en. [Accessed: 28- Oct- 2020].