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dc.contributorJohannessen, Tom C.en_GB
dc.date.accessioned2018-10-25T12:18:47Z
dc.date.available2018-10-25T12:18:47Z
dc.date.issued2004
dc.identifier844
dc.identifier.isbn82-464-0828-3en_GB
dc.identifier.other2004/00056
dc.identifier.urihttp://hdl.handle.net/20.500.12242/1703
dc.description.abstractThe pressure ratio, k, between the nozzle exitplane and the motorchamber, and the gas velocity at the nozzle exitplane, has been calculated. The results have been used to create propellant composition dependent expressions for these two parameters as a function of the nozzle expansion ratio. Theoretical pressure ratios, k, have been used together with experimental firing results to estimate the gas velocity at the nozzle exitplane. However, in four firings the pressure near the nozzle exitplane was measured, and the pressure ratio, k, from these measurements were compared with theoretical values. In order to conduct these measurements a new steel/molybdenum nozzle had to be constructed. The firings were performed with small scale rocket motors with radial burning grain (ca 0.3 kg). Two propellants with a slight performance difference, were used.en_GB
dc.language.isonoben_GB
dc.titleGasshastighet og trykk i en rakettmotors dyseutløp : beregninger og målingeren_GB
dc.subject.keywordRakettmotoreren_GB
dc.subject.keywordGassdynamikken_GB
dc.subject.keywordTrykkmålingen_GB
dc.source.issue2004/00056en_GB
dc.source.pagenumber32en_GB


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