航天推进技术研究院主办
[1]文 科,李旭昌,马岑睿,等.不同入口马赫数对超燃冲压发动机尾喷管的性能影响研究[J].火箭推进,2011,37(03):18-21.
WEN Ke,LI Xu-chang,MA Cen-rui,et al.Influence of nozzle inlet Mach number on performance of scramjet nozzle[J].Journal of Rocket Propulsion,2011,37(03):18-21.
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WEN Ke,LI Xu-chang,MA Cen-rui,et al.Influence of nozzle inlet Mach number on performance of scramjet nozzle[J].Journal of Rocket Propulsion,2011,37(03):18-21.
不同入口马赫数对超燃冲压发动机尾喷管的性能影响研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年03期
页码:
18-21
栏目:
研究与设计
出版日期:
2011-06-15
- Title:
- Influence of nozzle inlet Mach number on performance of scramjet nozzle
- 文章编号:
- 1672-9374(2011)03-0018-04
- 分类号:
- V235-34
- 文献标志码:
- A
- 摘要:
- 针对采用多目标优化方法设计的超声速燃烧冲压发动机非对称喷管，采用RNG k-ε湍流模型和有限体积方法数值求解有组分的守恒形式Navier-Stokes方程，数值模拟喷管不同入口马赫数条件下的喷管流场和性能。计算结果表明：喷管入口马赫数的变化会对喷管内流参数带来一定影响，导致喷管的推力和升力同时增大或减小，飞行器的配平性能可能会受到一定影响。
- Abstract:
- The RNG k-ε turbulence models and finite volume method were used to solve the conservative Reynolds-averaged Navier-Stokes equations and simulate the flow field and performance of the scramjet asymmetric ramp-nozzle designed with multi-target optimization method. The characteristics of the nozzle were numerically studied under the condition of various nozzle inlet Mach number. The simulation result shows that the variation of the nozzle inlet Mach number may influence the internal flow parameter of the nozzle, the increased or reduced inlet Mach number leads to up or down in thrust and lift force simultaneously, and maybe affects the stabilization of hypersonic air vehicle.
参考文献/References:
[1]EDWARDS C L W, SMALL W J, WEIDNER J P, et al. Studies of scramjet/airframe integ-ration techniques for hypersonic aircraft, AIAA 75-58 [R]. USA: AIAA, 1975.
[2]PERRIER P, RAPUC M, ROSTAND P. Nozzle and afterbody design for hypersonic airbreathing vehicles, AIAA 96-4548 [R]. USA: AIAA, 1996.
[3]GRONLAND T A, CAMBIER J L. Sensitivity to physical modeling for nozzle/afterbody flowfields, AIAA 96-4547[R]. USA: AIAA, 1996.
[4]晏至辉, 刘卫东, 超燃冲压发动机尾喷管数值分析[J]. 导弹与航天运载技术, 2006(5): 50-52.
[5]张艳慧, 徐惊雷, 张堃元. 超燃冲压发动机非对称喷管设计点性能 [J]. 推进技术, 2007, 28(3): 282-286.
[6]徐惊雷, 张艳慧, 张堃元. 超燃冲压发动机非对称喷管非设计点性能计算[J]. 推进技术, 2007, 28(3): 287-290.
[7]汪维娜, 王占学, 乔渭阳. 单斜面膨胀喷管几何参数对流场和性能的影响[J]. 航空动力学报, 2006, 21(2): 280-284.
[8]晏至辉. 超燃冲压发动机尾喷管仿真和试验研究[D]. 长沙: 国防科学技术大学, 2005.
[9]李建平, 宋文艳, 陈亮. 超燃冲压发动机尾喷管性能研究[J]. 机械设计与制造, 2008(6): 95-97.
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备注/Memo
收稿日期：2011-01-04；修回日期：2011-01-28
作者简介： 文科（1987—），男，硕士，研究领域为发动机内流场仿真与计算
更新日期/Last Update:
1900-01-01