[1]王振清,靳承滨,郝扣安,等.改良锥导乘波构型的数值研究[J].哈尔滨工程大学学报,2010,(06):0.
 WANG Zhen qing,JIN Cheng bin,HAO Kou an,et al.Numerical simulation of an improved conederived waverider[J].hebgcdxxb,2010,(06):0.
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改良锥导乘波构型的数值研究(/HTML)
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《哈尔滨工程大学学报》[ISSN:1006-6977/CN:61-1281/TN]

卷:
期数:
2010年06期
页码:
0
栏目:
出版日期:
2010-06-25

文章信息/Info

Title:
Numerical simulation of an improved conederived waverider
作者:
王振清 靳承滨 郝扣安 吕红庆
(哈尔滨工程大学航天与建筑工程学院,黑龙江哈尔滨150001)
Author(s):
WANG ZhenqingJIN ChengbinHAO KouanL Hongqing
(College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China)
关键词:
锥导乘波构型膨胀设计数值模拟气动性能流场特性
分类号:
V211.3
文献标志码:
A
摘要:
对乘波构型的上表面进行膨胀设计,并将膨胀角与其他设计参数一起进行优化,考察了由该方法生成的乘波构型的气动性能,采用数值模拟方法研究了一个带膨胀角的优化锥导乘波构型的外流场.控制方程取为雷诺平均NS方程,湍流模型取为标准kε模型,离散格式取为AUSM+格式,用有限体积法求解上述方程.模拟结果表明,在设计状态下用该优化方法生成的改良乘波构型流场前后均匀,下表面横向速度小,利于推进系统的安放;构型的迎角特性良好,适合巡航飞行,与设计初衷吻合.

参考文献/References:

[1]BOWCUTT K G, ANDERSON J D, CAPRIOTTI D. Viscous optimized hypersonic waveriders[C]// AIAA 87-0272. Reno, US, 1987.
[2]CORDA S, ANDERSON J D. Viscous optimized hypersonic waveriders designed from axisymmetric flow fields[C]//AIAA880369.Reno, US, 1988.
[3]KUCHEMANN D. The aerodynamic design of aircraft [M]. London: Pergamon Press, 1978: 448-510.
[4]NONWEILER T R F. Aerodynamic problems of manned space vehicle [J]. J of the Royal Areonautical Society, 1959, 63(9): 521-528.
[5]耿永兵,刘宏,姚文秀,王发民. 锥形流乘波体优化设计研究 [J]. 航空学报,2006,27(1):23-28.
GENG Yongbing, LIU Hong, YAO Wenxiu, WANG Famin. Viscous optimized design of waverider derived from cone flow[J]. Acta Aeronautica et Astronautica Sinica,
2006, 27(1):23-28.
[6]彭钧,陆志良,李文正. 乘波体气动性能综合优化[J]. 南京航空航天大学学报,2007,39(3):307-311.
PENG Jun, LU Zhiliang, LI Wenzheng. Upper/lower surface of waverider integrated optimization[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2007,39(3):307-311.
[7]张卫民,陈河梧,李新亚. 乘波外形高超声速风洞测力试验研究[J]. 实验流体力学,2005,19(4):16-19.
ZHANG Weimin, CHEN Hewu, LI Xinya. Investigation of waverider configuration in hypersonic wind tnnnel[J]. Experiments and Measur in Fluid Mechanics, 2005,19(4):16-19.
[8]范晓樯,李桦,李晓宇,田正雨. 高超声速乘波飞行器三维流场的并行数值模拟[J].国防科技大学学报,2003,25(2):5-8.
FAN Xiaoqing, LI Hua, LI Xiaoyu, TIAN Zhengyu. Parellel numerical simulation of the three dimensional flow field around the hypersonic waverider shape vehicle[J]. Journal of National University of Defense Technology, 2003,25(2):5-8.
[9]TRAVIS W D, IOANNIS N, GRAHAM V C. Numerical simulation of the AEDC waverider at mach 8[C]// AIAA 20062816. San Francisco,US,2006.
[10]DWAYNE J K. CFD Analysis of a generic waverider [C]// AIIA 20062817. San Francisco,US, 2006.
[11]SHVETS A I, VORONIN V I, BLANKSON I M. On waverider performance with hypersonic flight speed and high altitudes [C]// AIAA 2005512. Reno,US, 2005.〖ZK)〗[12]赵桂林, 胡亮, 闻洁. 乘波构形和乘波飞行器研究综述[J]. 力学进展, 2003, 33(3): 357-374.
ZHAO Guilin, HU Liang, WEN Jie. An overview of the research on waveriders and waverided derived hypersonic vehicles[J]. Advances in Mechanics, 2003, 33(3): 357-374.
[13]WANG Yankui, ZHANG Dongjun, Deng Xueying. The design of waverider configuration with high liftdrag ratio [C]// AIAA 20056040. San Francisco,US, 2005.
[14]WANG Zhenqing, ZHANG Cuie, HAO Kouan, et al. Expansion angle’s impact on the lift to drag ratio of the conederived wave rider [J]. Journal of Mechanics and MEMS, 2009, 1(2):419-425.
[15]NARUHISA T, MARK J L. NavierStokes computations of a viscous optimized waverider[J]. Journal of Space and Rockets, 1994, 31(3):383-391.

备注/Memo

备注/Memo:
教育部高等学校博士学科点专项科研基金资助项目(20060217010).
更新日期/Last Update: 2010-07-06