NACOR BWB

D150-BWB-2035

Key Characteristics

Research Category
Future Concept
Entry into Service
2035
Passengers
150
Range
4630
Wing Span
36
Maximum Take-Off Mass
66.7
Cruise Mach Number
0.78
Cruise Speed
838
Energy Carrier
Synth. Kerosene
Energy Consumption
14.8
Total Installed Power
132.1

With its distinctive design, the aircraft was developed as an alternative, highly aerodynamic, lightweight and therefore fuel efficient aircraft. The ultimate goal was to reduce the carbon footprint immensely. In this aircraft, the wing and fuselage appear to be “blended”. This means that the passengers will sit in the cabin, while the cargo bays, with the same capacity as conventional designs, will be located next to it. This concept has a wingspan of 36 metres to best meet the size restrictions of airport gates. With its relatively small size, it was quite unique at the time of its design.

These design features make the D150-BWB-2035 a research-driven exploration of alternative configurations for short-haul aviation.

The most important differences to today’s short-haul aircraft are listed below:

  1. Novel configuration of a blended wing body instead of tube and wing.
  2. Reduced engine noise compared to today’s aircraft as the aft engine is located on top of the centre body.

Advantages

  • Well-known superior aerodynamic performance compared to a conventional tube and wing configuration and therefore very fuel efficient
  • Combination of reflexed airfoils at the center body for pitch trim stability and supercritical airfoils at the outer wing to generate a near elliptic span wise lift distribution
  • Reduced engine noise in comparison to today’s aircraft due the aft engine is placed on top of the center body
  • Larger internal volume: the BWB offers increased payload capacity and flexibility in terms of interior configurations

Challenges

  • The longitudinal and lateral control of a BWB remains challenging but could be solved using advanced avionic systems and a well-designed movable layout
  • The number and location of emergency exits for embarking and disembarking of passengers remains challenging
  • It is a windowless cabin, yet passenger comfort has to be ensured
  • Detailed design issues, such as maintenance, airport compliance and operations, ditching, wing anti-icing

Project & Partners

The D150-BWB-2035 configuration was created in the NACOR project (New innovative Aircraft COnfigurations and Related issues, 2015-2022), in collaboration with the French aerospace lab ONERA, in the frame of the Clean Sky 2 Airframe ITD pillar. Clean Sky 2 is part of part of the European Commission's Horizon 2020 Research and Innovation Programme.
The project aim: identify the most promising short to medium range aircraft configuration among a plethora of conventional and unconventional air vehicle concepts, with the ultimate goal of significantly reducing carbon-footprint and fuel consumption in future aviation.

Outlook

Research is needed to address the detailed design and identify potential resulting challenges. Certification, windowless flying in relation to passenger comfort, emergency/exit plans and other aspects would need to be explored.

Key Characteristics

Mission and requirements

Year of Entry Into Service (EIS)
2035
Design Range
2500 NM
Design Cruise Mach Number
0.78
Design Mission Payload
17000 kg
Number of Passengers (Standard Layout)
150

Performance

Initial Cruise Altitude
3437 ft
Service Ceiling
3995 ft
Takeoff Balanced Field Length (SL, ISA conditions)
1900 m
Landing Field Length (SL, ISA conditions)
1741 m
Approach Speed (Calibrated Airspeed)
138 kts
Climb Speed (Calibrated Airspeed)
280 kts
Descent Speed (Calibrated Airspeed)
250 kts

Masses

Max Payload
20000 kg

Mass Breakdown

Share of the maximum take-off mass (MTOM 66.7 t)
Wing 23.8 % · 15.85 t
Engine 12.2 % · 8.11 t
OIM 8.5 % · 5.69 t
System 7.3 % · 4.84 t
Landing Gear 3.9 % · 2.61 t
Furnishing 2.2 % · 1.49 t
Pylon 1.1 % · 0.73 t
Fuel Block 12.9 % · 8.58 t
Fuel Reserve 2.7 % · 1.82 t
PAX 21.3 % · 14.23 t
Cargo 4.1 % · 2.75 t

Payload-Range Diagram

Payload over range
Payload-range limit Study missions
Show data as table
PointRange (NM)Range (km)Payload (t)
Limit0020.00
Limit1,5562,88120.00
Limit5,56510,3078.13
Limit6,25911,5920.00
Study mission2,0003,70413.61
Study mission2,5004,63017.00

References

Increasing Fuel Efficiency for Short to Medium Range Market: A Conceptual Aircraft Design Study on Unconventional Configuration.

Fröhler, Benjamin, Iwanizki, Michael, Woehler, Sebastian and Zill, Thomas

Download

Impact of the Number of Wing Stations on the Twist Distribution of a BWB Conceptual Aircraft Design in a MDAO Environment to Match Target Lift Distribution.

Fröhler, Benjamin and Iwanizki, Michael and Balack, Philip and Häßy, Jannik and Silberhorn, Daniel.

Download

Conceptual Design of a Blended-Wing-Body for a Short/Medium Range Mission Enhanced by High-Fidelity Aerodynamics.

Fröhler, Benjamin and Iwanizki, Michael and Zill, Thomas

Download

CONCEPTUAL DESIGN STUDIES OF UNCONVENTIONAL CONFIGURATIONS

Iwanizki, Michael and Wöhler, Sebastian and Fröhler, Benjamin and Zill, Thomas and Meheut, Michael and Defoort, Sebastien and Carini, Marco and Gauvrit-Ledogar, Julie and Liaboeuf, Romain and Tremolet, Arnault and Paluch, Bernard and Kanellopoulos, Stylianos

Download