scorpaena : Testing of a nitrous-oxide-ethanol bi-propellant rocket engine
About
Add a short description of your repository
Wiki
Data on a liquid bi-propellant rocket engine performance
A liquid bi-propellant rocket engine and supporting infrastructure has been designed, constructed, and tested at New Mexico Institute of Mining and Technology in a cooperative effort with Sandia National Laboratories [1]. The modular engine design consists of a head-end fuel-oxidizer injector, gaseous H2/O2 torch ignitor, combustion chamber, and nozzle modules. The robust modular design allows for rapid configuration changes and component replacement if damaged in testing. A permanently installed pressurizing system delivers liquid nitrous oxide and a variety of liquid fuels to the engine for both rocket engine development and propellant performance evaluation. Initial testing in the facility has explored the performance characteristics of nitrous oxide and ethanol as a potential green propellant system. Data acquisition includes dynamic pressure, temperature, and thrust measurements, with simultaneous high-speed schlieren imaging of the exhaust plume. Results are presented for varied combustion chamber pressures and propellant flow rates, yielding thrust in the range of 577 Newtons (130 pounds) force. The experimentally measured specific impulse for the nitrous-oxide/ethanol combination is in the range of 250 to 260 seconds. The experimental results compare well to theoretical predictions found using NASA CEA.
This repository contains data on ISP as a function of propellant mixture ratio and chamber pressure for nitrous oxide and ethanol. For each tested chamber pressure values functional relations of ISP vs O/F ratio are constructed.
Source:
[1] Jeff Phillip, Stewart Youngblood, Mark Grubelich, W Saul, Michael Hargather. Development and testing of a nitrous-oxide/ethanol bi-propellant rocket engine. 52nd AIAA/SAE/ASEE Joint Propulsion Conference. 2016. 10.2514/6.2016-5092.
Data on a liquid bi-propellant rocket engine performance
A liquid bi-propellant rocket engine and supporting infrastructure has been designed, constructed, and tested at New Mexico Institute of Mining and Technology in a cooperative effort with Sandia National Laboratories [1]. The modular engine design consists of a head-end fuel-oxidizer injector, gaseous H2/O2 torch ignitor, combustion chamber, and nozzle modules. The robust modular design allows for rapid configuration changes and component replacement if damaged in testing. A permanently installed pressurizing system delivers liquid nitrous oxide and a variety of liquid fuels to the engine for both rocket engine development and propellant performance evaluation. Initial testing in the facility has explored the performance characteristics of nitrous oxide and ethanol as a potential green propellant system. Data acquisition includes dynamic pressure, temperature, and thrust measurements, with simultaneous high-speed schlieren imaging of the exhaust plume. Results are presented for varied combustion chamber pressures and propellant flow rates, yielding thrust in the range of 577 Newtons (130 pounds) force. The experimentally measured specific impulse for the nitrous-oxide/ethanol combination is in the range of 250 to 260 seconds. The experimental results compare well to theoretical predictions found using NASA CEA.
This repository contains data on ISP as a function of propellant mixture ratio and chamber pressure for nitrous oxide and ethanol. For each tested chamber pressure values functional relations of ISP vs O/F ratio are constructed.
Source:
[1] Jeff Phillip, Stewart Youngblood, Mark Grubelich, W Saul, Michael Hargather. Development and testing of a nitrous-oxide/ethanol bi-propellant rocket engine. 52nd AIAA/SAE/ASEE Joint Propulsion Conference. 2016. 10.2514/6.2016-5092.
