The DLH25 introduces several advancements compared to today’s short-haul aircraft. The most notable one is its use of liquid hydrogen (LH2) as its primary energy source, instead of kerosene. To improve aerodynamic efficiency, the aircraft features an extended wingspan of 45 metres (instead of the usual 36 metres). This reducies drag and enhancesperformance.
The wing structure is made from carbon-fiber-reinforced polymer, a lightweight material that helps to lower the overall mass of the aircraft without compromising strength. Additionally, the DLH25 is equipped with an ultra-high bypass ratio turbofan engine, which significantly improves fuel efficiency and reduces emissions compared to traditional engines.
Hydrogen fuel tanks are integrated into the rear fuselage, instead of into the wing as it is usually the case with kerosene.
By providing a common LH2 aircraft definitionit the DLH25 concept contributes to advancing sustainable aviation technologies.
| Name | Unit | Value |
|---|---|---|
| Design Range | NM (km) | 2500 (4630) |
| Design Passenger Capacity | - | 239 |
| Design Cruise Mach Number | - | 0.78 |
| Max. Take-Off Mass (MTOM) | t | 93.4 |
| Max. Landing Mass | t | 88.3 |
| Maximum Zero-Fuel Mass | t | 87.0 |
| Operating Empty Mass (OEM) | t | 62.0 |
| Maximum Fuel Mass | t | 6.5 |
| Max. Payload | t | 25 |
| Wing Area | m² | 158.0 |
| Wing Span | m | 45.0 |
| Mean Aerodynamic Chord | m | 4.3 |
| Wing Loading (@ MTOM) | kg/m² | 591.3 |
| Thrust-to-Weight Ratio (@ ISA) | - | 0.331 |
| Engine Type | - | Turbofan |
| Thrust (Sea Level Static, ISA) | kN | 151.6 |
| Research Category | Baseline |
|---|---|
| Entry into Service | 2035 |
| Passengers | 239 |
| Range (km) | 4630 |
| Wing Span (m) | 45 |
| Maximum Take-Off Mass (t) | 93.4 |
| Cruise Mach Number | 0.78 |
| Cruise Speed (km/h) | 828.5 |
| Energy Carrier | LH2 |
| Energy Consumption | 17.9 |
| Total Installed Power (MW) | 42.5 |
