Improving inlet performance of turbo-ramjet engine by using surface correction
In this study axisymmetric supersonic intake model was tested at Mach number of 4. The intake geometry of SR-71 supersonic aircraft was used here for testing a scale model. Static and total pressure measurements in the duct were used to observe shock effect on internal flow. To improve pressure r...
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| 格式: | Thesis-Master by Coursework |
| 語言: | English |
| 出版: |
Nanyang Technological University
2021
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| 主題: | |
| 在線閱讀: | https://hdl.handle.net/10356/146359 |
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