Rocket Propulsion Facilities and R&D
NextAero has an established history in R&D rocket engine testing. We can handle the propellant complexity to make your project as easy and successful as possible. Come and test with us!
Sample Projects
Propellants We Work With
Fuels
- Liquid:
- Ethanol
- RP-1 Equivalent
- Coming Soon – Liquid Methane
- Coming Soon – Liquid Hydrogen
- Gaseous
- Compressed Natural Gas
- Hydrogen
- LPG
Oxidisers
- Liquid Oxygen (cryogenic)
- Gaseous Oxygen
- Nitrous Oxide
- Compressed Air
Static Propulsion Test Facilities
Short Duration Test Facility
20-1000kg thrust, 15 second duration
Nominal Propellants: LOX/Hydrocarbon (Ethanol, RP-1 Equivalent). Nitrous oxide possible on request.
Highly controllable oxidiser-fuel ratio.
Suitable for:
- University Projects and Research
- Rapid R&D
- Concept Studies
Outputs:
- 100-1kHz sampling to CSV data file
- Thrust, chamber pressure, temperature, any pressure throughout either propellant system.
Coming Soon – Long Duration Test Facility
Nominal Propellants: LOX/Hydrocarbon (Ethanol, RP-1 Equivalent)
20-1000kg Thrust, 120 second duration
Suitable For:
- Novel propulsion systems, proof of concept studies, full-duration studies, ablation and fatigue studies.
Coming Soon – Double Cryogenic Test Facility
Nominal Propellants: LOX – Liquid Methane/Liquid Hydrogen
20-1000kg Thrust, 120 second duration
Suitable for:
- Next generation propulsion system development
Available Rocket Engine Systems
Breadboard Rocket Engine
R&D Configurable
- Configurable bi-propellant injector
- Configurable combustion volume
- Configurable cooling geometry
Suitable for
- BYO rocket nozzle (e.g. converging-diverging, aerospike)
- Combustion performance studies
- Thermal barrier coating development
- Rapid performance envelope studies
Aerospike Nozzle
Converging Diverging Nozzle (Bell nozzle)