Numerical Simulation of a Supersonic and High Temperature Jet Impingement onto Flat Plate
| Autor: | Wei-ChengChen, 陳韋丞 |
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| Rok vydání: | 2019 |
| Druh dokumentu: | 學位論文 ; thesis |
| Popis: | 107 Since the impingement flow field of supersonic jet is extremely complex, it is impossible to directly observe detailed flow field phenomena using an experimental method. Therefore, in this study, the flow field analysis model, adopting the P-1 radiation model, is developed for the numerical simulation of exhaust plume of an actual solid-propellant rocket. The reliability of the above models was also confirmed through a relevant verification analysis. The jet impingement phenomenon, the temperature, and the heat flux on the plate for the numerical simulation of actual solid-propellant rockets exhaust plume are discussed. In a flow field verification analysis, the present results of the pressure distribution of the impinged plate and density-distribution contour of the impinging flow field for numerical simulation of nitrogen impingement were consistent with the experimental results, validating the present flow analysis model. A comparison of the SST k - omega turbulence model to k - epsilon turbulence model showed that the pressure distribution of the impinged plate obtained with the SST k - omega turbulence model was in more agreement with the experimental measurement values for the numerical simulation of the supersonic flow field. Furthermore, with some condition on the nozzle exit, the inside of the Mach disc was more prone to producing a recirculation zone when the exhaust jet was limited by the flat plate in the expansive flow stage. The main factor affecting the pressure distribution on the impinged plate was the existence of unstable recirculation zones. In the radiation model verification analysis, the temperature distribution taking the radiation effect into consideration was lower than the result without considering it in the high-temperature region. However, the result for the temperature distribution considering the radiation effect was higher than the result without considering it after the high-temperature region. Finally, the detailed flow field for the numerical simulation of actual solid-propellant rockets has been successfully predicted. It should be noted that the temperature distribution predicted with an assumed gaseous exhaust plume was substantially lower than the experimental measurement. However, after the impinging effect of alumina particles on the plate was taken into account, the estimated temperature distribution was shown to be in agreement with the experimental measurement. In other words, the influence of alumina particles in the exhaust plume was not negligible in predicting the temperature distribution of the impinged plate. |
| Databáze: | Networked Digital Library of Theses & Dissertations |
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