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International Journal of Energetic Materials and Chemical Propulsion

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

SEMI-ANALYTICAL MODEL FOR SUBSONIC TAILPIPE: EFFECTS ON SOLID ROCKET MOTOR PERFORMANCE

Volumen 13, Edición 2, 2014, pp. 97-110
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2014001411
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SINOPSIS

A review of one-dimensional steady-state equations was performed for the flow in a subsonic blast tube/tailpipe of a rocket motor. Assuming a constant diameter and only frictional losses, the analytical model that was derived from these equations is discussed. A simplified, semi-analytical model regarding internal ballistic effects was developed and is presented in spite of the complex set of chemical reactions between the combustion products from the motor chamber and the ablative liner, char-layer formation, and wall roughness variation. The trend of tailpipes leads to overestimating the characteristic velocity (C*) of the propellant and underestimating the thrust coefficient (CF) due to new stagnation conditions. Even for bell-shaped nozzles, the raw data after static firing tests have shown an appreciable loss in their performance. Some considerations have to be taken into account to compensate for these perturbations without jeopardizing the overall performance. The findings of this study are validated with data from firings of a real low-smoke propellant solid rocket motor.

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