[1]鞠玉涛,周长省,王政时.超声速轴对称双锥进气道流场数值模拟研究[J].南京理工大学学报(自然科学版),2005,(04):411-413.
 JU Yu-tao,ZHOU Chang-sheng,WANG Zheng-shi.Numerical Analysis on Flow Field of Supersonic Axisymmetric Double Cone-shaped Inlet[J].Journal of Nanjing University of Science and Technology,2005,(04):411-413.
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超声速轴对称双锥进气道流场数值模拟研究
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
期数:
2005年04期
页码:
411-413
栏目:
出版日期:
2005-08-30

文章信息/Info

Title:
Numerical Analysis on Flow Field of Supersonic Axisymmetric Double Cone-shaped Inlet
作者:
鞠玉涛周长省王政时
南京理工大学机械工程学院, 江苏南京, 210094
Author(s):
JU Yu-taoZHOU Chang-shengWANG Zheng-shi
School of Mechanical Engineering, NUST, Nanjing 210094, China
关键词:
进气道 冲压发动机 弹丸 数值模拟
Keywords:
inlets ramjets projectiles numerical simulation
分类号:
TJ410
摘要:
超声速轴对称双锥进气道流场数值模拟的控制方程为雷诺平均可压缩纳维尔-斯托克斯(Navier-Stokes)方程,数值格式为二阶迎风格式。对弹用双锥进气道流场进行了数值模拟,得到了清晰的流场结构。数值计算结果显示:进气道在来流马赫数为2.5时有较高的总压恢复系数,但是流量系数较低,来流马赫数为3时总压恢复系数有所降低,但流量系数增加较快,此时进气道仍然工作正常,说明双锥进气道能够满足冲压增程炮弹的使用要求。
Abstract:
Reynolds-averaged Navier-Stokes equations and second order windward scheme are used to simulate the supersonic axisymmetric double cone-shaped inlet. The characteristics of flow field in axisymmetric double cone-shaped inlet are numerically simulated and the flow structures are obtained. The results show that the total pressure recovery coefficient is relatively higher when the inflow Mach number is 2. 5, while the mass flow ratio is relatively lower. When the inflow Mach number is 3. 0, the total pressure recovery coefficient reduces, while the mass flow rat io increases rapidly, and the inlet still works well. The result suggests that the double cone-shaped inlet is applicable to the projectile with enhancement range by rocket ramjet.

参考文献/References:

[ 1] Knight D D. Improved calculation of high speed inlet flows [ R] . AIAA 80- 0383, 1980.
[ 2] 鞠玉涛, 武晓松. 轴对称阶梯型面管道内流场数值分析研究[ J] . 南京理工大学学报( 自然科学版) , 2001, 25 ( 3) : 238- 241.
[ 3] Sahu J. Computations of supersonic flow over a missile afterbody containing an exhaust jet[ R] . AIAA 85- 1815, 1985.
[ 4] Presley L L. Internal flow calculation for ax isymmetric supersonic inlets at angle of attack[ R] . AIAA 75- 1214, 1975.

相似文献/References:

[1]陈 雄,鞠玉涛,朱福亚.冲压增程弹用进气道试验与数值研究[J].南京理工大学学报(自然科学版),2007,(04):462.
 CHEN Xiong,JU Yu-tao,ZHU Fu-ya.Experimental and Numerical Research on Inlet of Ramjet Assisted Range Projectiles[J].Journal of Nanjing University of Science and Technology,2007,(04):462.
[2]陈 雄,周长省,郑 亚.侧向支柱对冲压增程弹用进气道性能影响研究[J].南京理工大学学报(自然科学版),2007,(05):541.
 CHEN Xiong,ZHOU Chang-sheng,ZHENG Ya.Influence of Strut Shapes on Performance of Ramjet Assisted Range Projectile Inlet[J].Journal of Nanjing University of Science and Technology,2007,(04):541.

备注/Memo

备注/Memo:
作者简介: 鞠玉涛( 1967- ) , 男, 山西太原人, 副教授, 博士, 主要研究方向: 火箭总体及火箭发动机技术, E-mail: zhouchsh @ mail. njust. edu. cn。
更新日期/Last Update: 2013-03-03