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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

EXPERIMENTAL STUDIES ON ROCKET EXHAUST PLUMES: SUPPORT FOR COMPUTED SIMULATION

Volumen 3, Edición 1-6, 1994, pp. 682-697
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.670
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SINOPSIS

Exhaust plumes of solid propellant missiles are heterogeneous flowfields containing gases and liquids or solid particles. Exhaust species mix with the atmosphere and may produce an afterburning flame. AP composite propellant combustion produces chloric acid which contributes to atmospheric water vapour condensation.
A missile exhaust plume has harmful operational consequences. It may disturb the missile guidance system and increase engine and launch platform detectability. Specific computer codes are used in order to simulate operational missile exhaust plume effects. Because these codes have to be verified, experimental techniques have been developed in order to characterize static rocket exhaust plumes. Radiation structure, radiance and temperature are measured by video, infrared and UV camera. Radiative chemical species are identified by spectroradiometry. Flowfield is studied by laser doppler anemometry and laser tomography. Collected smoke particles are analysed by electronic microscopy and X-ray spectrometry. Meteorological thresholds for water vapour condensation are noted for various propellant compositions.
Experimental setup, instruments and tested propellant are chosen in order to optimize comparisons between experimental results and numerical computations. Moreover, computer codes are modified to take experimental data into account.
Experimental and computed results allow establishment of correlations between exhaust plume characteristics, motor parameters and propellant compositions.

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