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- Publisher
- Springer Journals
- Copyright
- Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2022. corrected publication. Springer Nature or its licensor holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
- ISSN
- 2093-274X
- eISSN
- 2093-2480
- DOI
- 10.1007/s42405-022-00513-z
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- See Article on Publisher Site
Abstract
The characteristics of base drag and base flow were analyzed with the free-stream Mach number, chamber pressure, and nozzle divergence angle, through computational simulations. The numerical technique was validated through a comparison with a wind tunnel test. The results showed that base drag was affected by the nozzle divergence angle, free-stream flow, chamber pressure, and base flow was affected by the interaction of free-stream flow and the recirculation region generated at the base. In the over-expanded and relatively low under-expanded conditions, the expansion fan affects base drag, and base drag tends to be higher as the nozzle divergence angle is smaller. However, the opposite occurs when the Mach number is sufficiently low. In the highly under-expanded condition, the shock wave affects base drag, and base drag tends to be higher as the nozzle divergence angle is smaller. However, the main factors that affect base pressure can be varied in the high Mach number.
Journal
International Journal of Aeronautical and Space Sciences – Springer Journals
Published: Nov 1, 2022
Keywords: Base drag; Base pressure; Base flow; Nozzle divergence angle; NPR