高超声速飞行器后体喷管设计

留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名

邮箱

手机号码

标题

留言内容

验证码

Nozzle afterbody design of hypersonic flight vehicle

Shool of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

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.
- 航空、航天推进系统 /
- 高超声速 /
- 后体喷管 /
- 数值模拟 /
- 膨胀波
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.
- aerospace propulsion system /
- hypersonic /
- nozzle afterbody /
- numerical simulation /
- expansion wave

[1]	刘陵.超声速燃烧与超声速燃烧冲压发动机[M].西安:西北工业大学出版社,1993.
[2]	Edwards C L Q,Small W J,Weidner J P.Studies of scramjet/airframe integration techniques for hyper-sonic aircraft[R].AIAA-75-58.
[3]	潘锦珊.气体动力学基础[M].北京:国防工业出版社,1988.
[4]	李人宪.有限体积法基础[M].北京:国防工业出版社,2005.

点击查看大图