[1]郑健,周长省,鞠玉涛,等.弧形翼-身组合体绕流流场数值模拟及实验研究[J].南京理工大学学报(自然科学版),2012,36(03):505-510.
 ZHENG Jian,ZHOU Chang-sheng,JU Yu-tao.Experimental Study and Numerical Simulation of Flow Field over Wrap-around Fin-body Combination[J].Journal of Nanjing University of Science and Technology,2012,36(03):505-510.
点击复制

弧形翼-身组合体绕流流场数值模拟及实验研究
分享到:

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
36卷
期数:
2012年03期
页码:
505-510
栏目:
出版日期:
2012-06-30

文章信息/Info

Title:
Experimental Study and Numerical Simulation of Flow Field over Wrap-around Fin-body Combination
作者:
郑健; 周长省; 鞠玉涛;
南京理工大学机械工程学院;
Author(s):
ZHENG JianZHOU Chang-shengJU Yu-tao
School of Mechanical Engineering,NUST,Nanjing 210094,China
关键词:
弧形翼 翼-身组合 流场 雷诺应力湍流模型 平流迎风劈裂法 吹风实验
Keywords:
wrap-around fin fin-body combination flow field Reynolds stress turbulence model advection upwind splitting method flow test
分类号:
V211.4
摘要:
为了研究标准技术协作计划(TTCP)弧形翼-身组合体的空气动力学特性,对其在超声速下的三维绕流流场进行了数值模拟。应用雷诺应力湍流模型和平流迎风劈裂法离散格式,对弧形翼-身组合体在Ma∈[2.0,5.5]范围内的超声速绕流流场结构进行了分析。计算分析了弧形翼-身组合体的各气动力系数随马赫数、攻角的变化规律。阐述了弧形翼在零攻角状态下产生自诱导滚转力矩的机理。利用超声速风洞进行了标准TTCP弧形翼-身组合体在Ma=3.0条件下的吹风实验。实验结果与数值模拟结果的计算误差小于10%,验证了所采用数值模拟方法的可信度。
Abstract:
To study the aerodynamic characteristics of the technical cooperation program(TTCP)standard wrap-around fin(WAF)-body combination,the three-dimensional supersonic flow over it is numerically simulated.In the range of Ma∈[2.0,5.5],the supersonic flow field structure of the WAF-body combination is analyzed by using the Reynolds stress turbulence model and advection upwind splitting method discrete scheme.The change rules of the WAF-body combination aerodynamic coefficients with Mach numbers,angles of attack are calculated and analyzed.The mechanism of self-induced roll moment produced at zero attack angle is analyzed.The flow tests of the standard TTCP WAF-body combination are conducted in the condition of Ma=3.0 by a supersonic wind tunnel.The calculation error between the numerical simulation results and wind tunnel test ones is less than 10%,which verifies the credibility of the numerical simulation method.

参考文献/References:

[1] Wardlaw A B,Priolo F J,Solomon J M. Multiple-zone strategy for supersonic missiles [J]. Journal of Spacecraft and Rockets, 1987, 24( 4) : 377-384.
[2] Harris L E. Computation of the roll moment coefficient for a projectile with wrap-around fins ( AIAA - 93 - 0499) [R]. Monterey,USA: AIAA Paper, 1993: 1-7.
[3] Tilmann C P,Huffman R E,Buter T A, et al. Characterization of the flow structure in the vicinity of a wrap-around fin at supersonic speeds( AIAA-96-0190) [R]. Monterey,USA: AIAA Paper, 1996: 1-10.
[4] Tilmann C P,Bowersox R D W. Characterization of the flow field near a wrap-around fin at mach 4. 9( AIAA-98 -0684) [R]. Monterey,USA: AIAA Paper, 1998: 1-11.
[5] 鞠玉涛. 弧形翼-身组合体空气动力特性的数值模拟研究[D]. 南京: 南京理工大学机械工程学院, 1999.
Ju Yutao. Numerical simulation of aerodynamic characteristic of projectile with WAF[D]. Nanjing: School of Mechanical and Engineering,Nanjing University of Science and Technology, 1999.
[6] 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,2005, 29( 4) : 411-413.
Ju Yutao, Zhou Changsheng, Wang Zhengshi. Numerical analysis on flow field of supersonic axisymmetric double cone-shaped inlet[J]. Journal of Nanjing University of Science and Technology,2005,29 ( 4) : 411-413.
[7] 宋旭民,夏刚,秦子增. 卷弧翼弹零攻角流场数值模拟[J]. 战术导弹技术, 2002, 23( 6) : 21-24.
Song Xumin,Xia Gang,Qin Zizeng. Numerical simulation of flow field for wraparound fins projectile at zero angle of attack[J]. Tactical Missile Technology, 2002, 23( 6) : 21-24.
[8] 刘巍. 卷弧尾翼弹气动特性研究[D]. 长沙: 国防科技大学航天与材料工程学院, 2005.
Liu Wei. Research on the aerodynamic characteristics of the projectile with wrap around fins[D]. Changsha: School of Aerospace and Materials Engineering, National University of Defense Technology, 2005.
[9] Gregg L A,Theresa C. Analysis of missile configurations with wrap-around fins using computational fluid dynamics( AIAA-93-3631-CP) [R]. Monterey,USA: AIAA Paper, 1993: 157-166.
[10] 陆中兵,丁珏,周彦煌,等. 超声速飞行底部排气弹三维湍流流场数值模拟[J]. 南京理工大学学报, 2007, 31( 1) : 27-30.
Lu Zhongbing,Ding Jue,Zhou Yanhuang, et al. Numerical inwestigation of 3-d turbulet flow fields for supersonic flying base bleed projectile [J]. Journal of Nanjing University of Science and Technology,2007, 31( 1) : 27-30.
[11] John E W,Robert H K. Supersonic interaction in the corner of intersecting wedges at high Reynolds numbers[J]. AIAA-Journal, 1972, 10( 10) : 652-656.
[12] 曹从咏,江坤. 复杂外形火箭导弹三维绕流与喷流干扰流场的数值模拟[J]. 南京理工大学学报, 2005, 29( 3) : 264-266.
Cao Congyong, Jiang Kun. Numerical simulation of interactive flowfield between jet and external flow around rocket /missile with complex shape[J]. Journal of Nanjing University of Science and Technology,2005,29 ( 3) : 264-266.
[13] 钱杏芳,林瑞雄,赵亚男. 导弹飞行力学[M]. 北京: 北京理工大学出版社, 2008.

更新日期/Last Update: 2012-10-12