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Thermal freezing in the technology of aerospace propelants

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dc.contributor.author RUGESCU, R. D.
dc.date.accessioned 2019-07-24T10:17:17Z
dc.date.available 2019-07-24T10:17:17Z
dc.date.issued 2005
dc.identifier.citation RUGESCU, R. D. Thermal freezing in the technology of aerospace propelants. In: Meridian Ingineresc. 2005, nr. 4, pp. 25-30. ISSN 1683-853X. en_US
dc.identifier.issn 1683-853X
dc.identifier.uri http://repository.utm.md/handle/5014/3751
dc.description.abstract The thermal freezing phenomenon was occasionally identified during an early experimental verification of shifting equilibrium rocket flow computations. The manner by which the value of 1671÷36ºK for this temperature was extracted from repeated chromatographic experiments is presented. Numerical simulation of combustion and propulsion processes got a high accuracy level when this process was included in the computer codes. en_US
dc.description.abstract Fenomenul îngheţării termice a fost identificat întâmplător în timpul unei verificări timpurii a calculelor curgerii în echilibru chimic alunecător în motoare rachetă. Este prezentată maniera prin care valoarea de 1671÷36ºK pentru această temperatură a fost extrasă din experimente cromatografice repetate. Simulările numerice ale combustiei şi proceselor de propulsie au căpătat un înalt nivel de acurateţe când acest proces a fost inclus în codurile de calcul. ro
dc.description.abstract Le phénomène des froidement thermique a été accidentellement identifie durant une en vérification expérimentale du calculassions des écoulements en équilibre glissant dans les moteurs fusées. La manière dans laquelle la valeur de 1671÷36ºK pour cet température a était extractee par d'expérimentes chromatographiques répétée est présentée. Des simulations numériques de combustion et de processus de propulsion avoir obtenu un niveau élevait de précision quant cette processus avoir être inclue dans de codes computationnelle. fr
dc.description.abstract Феномен термического замораживания был случайно открыт во время одной ранней проверки расчётов течения в скользящем химическом равновесии в ракетных двигателях. Приведён метод, при котором значение 1671÷36ºK для этой температуры было извлечено из повторяющихся хроматографических экспериментов. Численное моделирование сгорания и движительных процессов получили высокую точность когда этот процесс был включён в расчетных программах. ru
dc.language.iso en en_US
dc.publisher Editura U.T.M. en_US
dc.rights Attribution-NonCommercial-NoDerivs 3.0 United States *
dc.rights.uri http://creativecommons.org/licenses/by-nc-nd/3.0/us/ *
dc.subject aerospace propellants en_US
dc.subject thermal freezing en_US
dc.subject rocket engines en_US
dc.subject îngheţare termică en_US
dc.subject motoare rachetă en_US
dc.subject propulsie en_US
dc.subject propulsanţi aerospatiali en_US
dc.title Thermal freezing in the technology of aerospace propelants en_US
dc.title.alternative Inghetarea termica in tehnologia propulsantilor aerospatiali en_US
dc.title.alternative Le froidement thermique dans la technologie des propellants aérospatiales en_US
dc.title.alternative Термическое замораживание в технологии воздушно-космических движителей en_US
dc.type Article en_US


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