Commuter Aircraft

GA9-TP

Key Characteristics

Research Category
Baseline
Entry into Service
Today
Passengers
9
Range
600 km
Wing Span
12.8 m
Maximum Take-Off Mass
3.16 t
Cruise Mach Number
0.25
Cruise Speed
300 km/h
Energy Carrier
Synth. Kerosene
Energy Consumption
39.9 kWh/pax/100 km
Total Installed Power
0.47 MW

The Commuter Aircraft is a concept for a modern 9-seater twin-turboprop aircraft configuration, designed with a low-wing and a T-shaped tail and built for efficient short commuter flights (up to 600 kilometres).

This design represents the current state of the art. It serves as a basis for exploring how new technologies and configurations can improve the performance of future aircraft. By comparing key results of this basic concept with those of new designs, the effects of novel technologies can be estimated. Many current aircraft of the certification class EASA CS-23 still rely on technology from the 1970s and 1980s, so the introduction of more advanced solutions has the potential to significantly improve fuel efficiency, speed and overall performance. The concept is based on the design of the Cessna 441, a model that entered service in 1977, but with updated cabin geometry and mission requirements for low-density commuter flights between small airports.

This concept represents an intermediate step between reference and baseline aircraft concepts, in that it represents the current generation technology and does not include any assumptions about future technology advancements.

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

None, the Commuter Aircraft is an interpretation of a current aircraft.

Advantages

  • Simple design and proven technology
  • High technological maturity leads to low risk for manufacturing, certification and operation

Challenges

  • Very low potential of climate impact reduction due to current state-of-the-art technology level
  • No benefits in energy efficiency over the current state
  • Questionable public acceptance in the future

Project & Partners

The aircraft was developed within the D-Light project as a design basis to evaluate the performance of a hydrogen-electric commuter aircraft concept.

Outlook

The aircraft concept will be matured into a research baseline with a projected technology level of 2030. To achieve this, technology factors will be introduced for relevant aircraft parametres, such as fuel efficiency, or mass. The aim of the concept is to serve as a baseline for performance evaluations of new technologies developed in current and future projects.

Key Characteristics

Mission and requirements

Design Range
324 NM
Design Passenger Capacity
9
Design Cruise Mach Number
0.25

Masses

Max. Take-Off Mass (MTOM)
3164 kg
Max. Landing Mass
3164 kg
Max. Zero-Fuel Mass
2951 kg
Operating Empty Mass (OEM)
2041 kg
Maximum Fuel Mass
515 kg
Max. Payload
855 kg

Geometry and cabin

Wing Area
15.5 m
Wing Span
12.8 m
Mean Aerodynamic Chord
1.2 m
Wing Loading (at MTOM)
204.1 kg/m^2

Propulsion and energy

Power-to-Weight Ratio (at ISA)
0.15 kW/kg
Engine Type
Turboprop
Shaft Power (at Sea Level, ISA)
471 kW

Mass Breakdown

Share of the maximum take-off mass (MTOM 3.2 t)
System 18.7 % · 0.59 t
Engine 12.9 % · 0.41 t
Fuselage Structure 10.1 % · 0.32 t
Wing 8.4 % · 0.26 t
Furnishing 7.7 % · 0.24 t
Landing Gear 3.5 % · 0.11 t
OIM 1.4 % · 0.04 t
VTP 1.0 % · 0.03 t
HTP 0.9 % · 0.03 t
Fuel Block 5.7 % · 0.18 t
Fuel Reserve 2.8 % · 0.09 t
PAX 27.0 % · 0.85 t
Cargo 0.0 % · 0.00 t

Payload-Range Diagram

Payload over range
Payload-range limit Study missions
Show data as table
PointRange (NM)Range (km)Payload (t)
Limit000.91
Limit2184040.91
Limit8111,5010.61
Limit8941,6560.00
Study mission3246000.86