This script is to be used to develop a small liquid bi-propellant rocket engine. It has been tested to be operational for the design of a 150 [lbf] liquid rocket engine using nitrous oxide and isopropanol as the propellants.
TODO List
- Selections of various efficiencies
- Nozzle efficiency remaining
- Ability to tune CEA output towards a specific combustion temperature
- Method of Characteristics Implementation (WIP)
- Engine Volume/Weight from Variable thickness