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.
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.
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)