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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.
This paper develops a robust and practical design for supersonic nozzles to be used in an altitude engine test facility.
The flow-fields and thrust of the aerospike nozzle, for the full and truncated nozzles, were investigated.
The purpose of this study is to investigate other rocket nozzles that might have the ability to improve performance of a propulsion system without a large penalty on vehicle mass or cost.
Preliminary design optimal techniques were adopted to reduce nozzle length while keeping the exit area constant in the design.