| 高超声速飞行器后体喷管设计 |
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| 引用本文： | 徐华松,谷良贤.高超声速飞行器后体喷管设计[J].航空动力学报,2007,22(2):257-260. |
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| 作者姓名： | 徐华松 谷良贤 |
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| 作者单位： | 西北工业大学,航天学院,西安,710072 |
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| 摘 要： | 为得到二维高超声速飞行器后体喷管优化型面,建立了基于N-S方程的二维后体喷管设计模型,分别对内部喷管长度和上壁型面进行设计,得到了后体喷管优化设计外形,并将结果与Edwards提供的基准进行比较,表明改进了后体喷管的推进性能.
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| 关 键 词： | 航空、航天推进系统 高超声速 后体喷管 数值模拟 膨胀波 高超声速飞行器 喷管设计 hypersonic flight vehicle design 推进性能 改进 比较 基准 结果 外形 优化设计 壁型 长度 设计模型 方程 后体喷管 |
| 文章编号： | 1000-8055(2007)02-0257-04 |
| 收稿时间： | 2005/12/28 0:00:00 |
| 修稿时间： | 2005年12月28 |
Nozzle afterbody design of hypersonic flight vehicle |
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| XU Hua-song and GU Liang-xian.Nozzle afterbody design of hypersonic flight vehicle[J].Journal of Aerospace Power,2007,22(2):257-260. |
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| Authors: | XU Hua-song and GU Liang-xian |
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| Institution: | Shool of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;Shool of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China |
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| Abstract: | A model based on numerical solution of Navier-Stokes equations was established for hypersonic flight vehicle nozzle afterbody optimization design.The internal portion and the upper wall of nozzle were designed,and the optimized configuration was obtained.The result was compared to the norm configuration that Edwards claimed.The results show that the performance of nozzle afterbody was improved. |
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| Keywords: | aerospace propulsion system hypersonic nozzle afterbody numerical simulation expansion wave |
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