An igniter for a LOX/CH4 rocket engine is designed and a CFD model is developed which is used to model the designed igniter.Verification and validation methods are discussed.... To launch a rocket to the edge of space using a pressure fed rocket system with liquid oxygen as propellant, you need to know exactly how much pressurant gas (helium) you need to take along.However, such systems are still in an early development phase and one of the key areas requiring further investigations is the operation of the magnetic nozzle, the device meant to...
Preliminary design optimal techniques were adopted to reduce nozzle length while keeping the exit area constant in the design.
Optimization produced a smooth flow by generating a parallel and uniform flow at the exit. in Aeronautical Engineering from Seoul National University in 19, respectively. D from the University of Illinois in Urbana-Champaign in 1992. Lee is currently a Professor at the Department of Aerospace Engineering in Konkuk University in Seoul, Korea.
Based on the information presented in this thesis, university-based satellite teams can manipulate the inputs of the design and analysis methods to investigate the use of an aerospike nozzle design concept to meet their design goals"--Abstract, page iii.
The German Aerospace Centre (DLR) has in the past years been performing test runs with their experimental sub-scale combustion chambers to measure and investigate the effects of unstable combustion.
Some of these investigations are focused on the heat flux to the chamber walls, changes in which can cause a significant shift in chamber wall...