Zobrazeno 1 - 6
of 6
pro vyhledávání: '"Yoon-Wan Moon"'
Publikováno v:
Journal of the Korean Society of Propulsion Engineers. 23:101-106
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::34791f2519f76edf56e16c1e9212db45
https://doi.org/10.6108/kspe.2019.23.5.101
https://doi.org/10.6108/kspe.2019.23.5.101
Publikováno v:
Transactions of the Korean Society of Mechanical Engineers B. 34:817-824
An improved spray model of a pressure-swirl atomizer was developed and the grid dependency of the model was investigated. Since the Lagrangian-Eulerian approach was adopted for tracking droplets, very small grids could not be used. However, in order
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8306460ed0b60358e1a615e730e97b61
https://doi.org/10.3795/ksme-b.2010.34.9.817
https://doi.org/10.3795/ksme-b.2010.34.9.817
Publikováno v:
Transactions of the Korean Society of Mechanical Engineers B. 34:563-568
초록:30톤급액체산소/케로신액체로켓엔진개발의중간단계로터보펌프-가스발생기개회로연계시험이수행되었다.터보펌프-가스발생기개회로연계시험은엔진시스템작동모사환경시험으로서가
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6f85746f503f5255e8232e5e1072b0a8
https://doi.org/10.3795/ksme-b.2010.34.5.563
https://doi.org/10.3795/ksme-b.2010.34.5.563
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 32:93-101
A method to calculate stability limits is investigated to predict the characteristics of high-frequency combustion instability in liquid-propellant rocket engine. It is based on the theory of linear stability analysis proposed in previous works and u
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cf65bbd8eb212eeb329d8e029aa18346
https://doi.org/10.5139/jksas.2004.32.10.093
https://doi.org/10.5139/jksas.2004.32.10.093
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 32:80-87
To understand the each performance parameter correlation of flight type liquid-propellant rocket engine for KSR-III(Korea Sounding Rocket-III), the analysis of engine stand-alone combustion test results was carried out. Considering the variation of a
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::865167f77b1c764a6b58e5d4e48a1489
https://doi.org/10.5139/jksas.2004.32.4.080
https://doi.org/10.5139/jksas.2004.32.4.080
Publikováno v:
Journal of the Korean Society for Aeronautical & Space Sciences. 30:46-52
Characteristics of flow rate control has been studied for a cavitating venturi adopted in a liquid rocket propellant feed system. Both experiment and numerical simulation have been performed to give about 10% discrepancy of mass flow rate for cavitat
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::450c2fe6082ad7238ab1ee54ab16e195
https://doi.org/10.5139/jksas.2002.30.6.046
https://doi.org/10.5139/jksas.2002.30.6.046