高速条件下细长旋成体背风区流动特性试验研究

doi:10.12382/bgxb.2022.0688

摘要/Abstract

摘要：

导弹全方向攻击时会产生由旋涡主导的复杂流动,发生转捩和流动分离,对导弹的机动性和控制能力具有重大影响。为探索攻角及马赫数对弹体流动形态的影响,针对某细长旋成体在FD-12风洞开展高速粒子图像测速及荧光油流试验,来流Ma分别为0.4、0.6、0.8,攻角范围α为0°~180°,获取了细长体背风区的流场特性演化规律。研究结果表明:当攻角α<90°时,随着攻角的增大,模型背风区流场从附着流变化为分离流,且分离涡从对称变为非对称,最终演化为非定常流动;当攻角α>90°时,情况有所不同,α=100°及α=120°时背风区存在非定常涡脱落现象,时均流场具有明显的非对称性;当攻角α=150°时,迎风面分离区出现不对称偏移,初始分离区下边界已越过模型端面,在模型中后部形成分离线;当攻角α=180°时,时均流场没有明显的特征,在模型头部位置出现了环形分离区及再附区,表明由于底部扰动的影响,该截面流场呈现局部的非定常、非线性流动状态;在攻角相同情况下,增大流场的来流Ma,不但会使分离涡的影响范围变大,也会导致分离涡的位置抬高。

关键词: 细长体, 大攻角, 粒子图像测速, 流动分离, 旋涡

Abstract:

The transition and flow separation dominated by vorticity will occur, which have a significant impact on the maneuverability and control ability of missile, when a missile launches an all-aspect attack. The particle image velocimetry (PIV) and fluorescent oil flow visualization experiments are carried out in the FD-12 wind tunnel for a slender body in order to explore the influences of angle of attack and Mach number on the flow pattern in the leeward region of slender body.The characteristics of the flow field in the leeward region of slender body were obtained at the angles of attack α from 0° from180° with Ma=0.4/0.6/0.8. The results show that the flow in the leeward region of the model changes from attached flow to separation flow, and the separation vortex vary from symmetry to asymmetry when the angle of attack is <90°. The unsteady vortex shedding phenomenon exists in the leeward region and the time-averaged flow field has an obvious asymmetry characteristic at 100° and 120° angles of attack. The separation zone of windward face begins to appear asymmetric offset for α=150°. The lower boundary of initial separation zone crosses the end face of the model, forming a separation line in the rear of the model. When the angle of attack changes to 180°, there is an obvious ring-shaped separation zone and re-attachment zone at the upwind face and no obvious separation zone at the rear of the model. The results indicate that the flow field presents complex unsteady and nonlinear flow states due to the influence of bottom. In addition, the increase of the Mach not only enlarge the influence range of separation vortex, but also promote the position of separation vortex at the same angle of attack.

Key words: slender body, high angle of attack, particle image velocimetry, flow separation, vortex

中图分类号:

TJ590

李晓辉, 王宏伟, 熊红亮, 石伟龙, 任少洁, 黄湛. 高速条件下细长旋成体背风区流动特性试验研究[J]. 兵工学报, 2024, 45(3): 818-827.

LI Xiaohui, WANG Hongwei, XIONG Hongliang, SHI Weilong, REN Shaojie, HUANG Zhan. Experimental Study on the Flow Characteristics of a Slender Body of Revolution in the Leeward Region under High-speed Condition[J]. Acta Armamentarii, 2024, 45(3): 818-827.

图/表 23

图1 试验模型

Fig.1 Experimental model

图2 模型安装示意图(左为模型正装,右为模型反装)

Fig.2 Model installation(left: model suits; right: model reversal)

表1 模型预置攻角状态

Table 1 Model preset angle of attack

预偏攻角/(°)	可实现攻角状态/(°)	模型部件更换
15	0~40	正装
75	60~100	正装
75	80~120	反装
15	140~180	反装

表2 试验工况

Table 2 Experimental conditions

Ma	攻角α/(°)	z/mm	试验手段
0.6	0	6.83D	PIV
0.4	30	6.83D	PIV
0.6	30	6.83D	PIV
0.8	30	6.83D	PIV
0.6	60	6.17D	PIV
0.4	80	6.17D	PIV
0.6	80	6.17D	PIV
0.8	80	6.17D	PIV
0.6	100	4D	PIV
0.6	120	4D	PIV
0.6	150	4D	PIV
0.6	180	4D	PIV
0.6	100		油流
0.6	120		油流
0.6	150		油流
0.6	180		油流

图3 相机内置方案

Fig.3 Camera built-in scheme

图4 油流试验拍摄布局

Fig.4 Experimental layout of oil film

图5 粒子图像及速度流线图分布(左:粒子图像;右:速度分布)

Fig.5 Particle image and velocity flow distribution (left: particle image; right: velocity distribution)

图6 粒子图像及速度流线图分布(左:粒子图像;右:速度分布)

Fig.6 Particle image and velocity flow distribution (left: particle image; right:velocity distribution)

图7 粒子图像及速度流线图分布(左:粒子图像;右:速度分布)

Fig.7 Particle image and velocity flow distribution (left: particle image; right: velocity distribution)

图8 Ma=0.4时空间流动结构(左:粒子图像;中:瞬时速度分布;右:时均速度分布)

Fig.8 Spatial flow structure for Ma=0.4(left: particle image; middle:instantaneous velocity distribution; right : time-averaged velocity distribution)

图9 Ma=0.6时空间流动结构(左:粒子图像;中:瞬时速度分布;右:时均速度分布)

Fig.9 Spatial flow structure for Ma=0.6(left: particle image; middle:instantaneous velocity distribution; right: time-averaged velocity distribution)

图10 Ma=0.8时空间流动结构(左:粒子图像;中:瞬时速度分布;右:时均速度分布)

Fig.10 Spatial flow structure for Ma=0.8(left: particle image; middle:instantaneous velocity distribution; right: time-average velocity distribution)

图11 时均涡量分布图(左:Ma=0.4;中:Ma=0.6;右:Ma=0.8;α=30°)

Fig.11 Time-averaged vorticity distribution diagram(left:Ma=0.4;middle:Ma=0.6;right:Ma=0.8;α=30°)

图12 背风区涡量变化图(α=30°)

Fig.12 Diagram of leeward vorticity variation(α=30°)

图13 涡核距模型截面中心垂直距离随Ma变化(α=30°)

Fig.13 Vertical distance between vortex core and the center of model section vs. Mach number(α=30°)

图14 旋涡涡核水平距离随Ma变化(α=30°)

Fig.14 Horizontal distance of vortex core vs. Mach number(α=30°)

图15 瞬时涡量分布图(上:Ma=0.4;中:Ma=0.6;下:Ma=0.8;α=80°)

Fig.15 Instantaneous vorticity distribution diagram(upper:Ma=0.4;middle:Ma=0.6;below:Ma=0.8;α=80°)

图16 分离涡随攻角变化情况(Ma=0.6)

Fig.16 Separation vortex vs. angle of attack(Ma=0.6)

图17 模型表面流动图谱

Fig.17 Flow pattern of model

图18 分离周向角计算示意图

Fig.18 Calculation method of separation angle

图19 分离位置(图中数字为像素长度)

Fig.19 Separation position(the numbers are pixel length)

表3 分离周向角计算

Table 3 Calculated results of separation angle

α/(°)	z/D
α/(°)	1	2	3	4	5	6
100	101.31	101.11	103.57	104.62	101.58	102.16
120	106.45	105.11	109.90	109.32	106.05	106.95

图20 分离周向角沿流向变化

Fig.20 Change of separation angle along the flow direction

参考文献 24

[1]	宋琛, 张俊宝, 张蓬蓬. 反作用射流控制技术在空空导弹上的应用研究[J]. 电光与控制, 2020, 27(7):68-71.
	SONG C, ZHANG J B, ZHANG P P. Application of reaction jet control technology to air-to-air missile[J]. Electronics Optics & Control, 2020, 27(7):68-71. (in Chinese)
[2]	HUNT B L. Asymmetric vortex forces and wakes on slender bodies[R]. Reston, VA, US:AIAA, 1982.
[3]	ZILLIAC G G, DEUANI D, TOBAK M. Asymmetric vortices on a slender body of revolution[J]. AIAA Jourrnal, 1991, 29(5):667-675.
[4]	DEUANI D, TOBAK M. Numerical, experimental, and theoretical study of convective instability of flow over pointed bodies at incidence[R]. Edwards,CA,US:Reston, VA, US:AIAA, 1991.
[5]	BJARKE L J, DEL FRATE J H, FISHER D F. A summary of the forebody high-angle-of-attack aerodynamics research on the F-18 and the X-29A aircraft[R]. AE Technical Paper Series,SAE International Aerospace Technology Conference and Exposition, 1992.
[6]	MURMAN S M. Geometric perturbations and asymmetric vortex shedding about slender bodies[R]. Reston, VA,US:AIAA, 2000.
[7]	刘沛清, 邵延峰, 邓学蓥, 等. 大迎角细长旋成体绕流结构演变过程实验研究[J]. 航空学报, 2003, 24(6):503-506.
	LIU P Q, SHAG Y F, DENU X Y, et al. Experimental study of evolutionary process of the flow field around slender body at high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2003, 24(6):503-506. (in Chinese)
[8]	杨云军, 崔尔杰, 周伟江. 压缩性对细长体涡流非对称发展的影响[J]. 航空学报, 2004, 25(4):333-338.
	YANG Y J, CUI E J, ZHOU W J. Effects of compressibility on the asymmetry development of vortex flow around a slender body[J]. Acta Aeronautica et Astronautica Sinica, 2004, 25(4):333-338. (in Chinese)
[9]	ZHOU N C, YE Z Y, HU H D. Asymmetric vortex structure of slender revolution at high angles of attack[J]. Acta Aerodynamica Sinica, 2004, 22(4):486-493. (in Chinese)
[10]	THOMSON K D, MORRISON D F. The spacing, position and strength of vortices in the wake of slender cylindrical bodies at large incidence[J]. Journal of Fluid Mechanics, 1971, 50(4):751-783. doi: 10.1017/S0022112071002878 URL
[11]	LOWSON M V, PONTON A J C. Symmetry breaking in vortex flows on conical bodies[J]. AIAA Journal, 1992, 30(6):1576-1583. doi: 10.2514/3.11103 URL
[12]	顾蕴松. 大攻角前体非对称流动的控制技术[D]. 南京: 南京航空航天大学, 2005.
	GU Y S. Control techniques for asymmetric flow of precursors at high angles of attack[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005. (in Chinese)
[13]	HALL I M, ROGERS W E, DAVIS B M. Experiments with inclined blunt nosed bodies at M=2.45[R]. London, UK: H.M. Stationary Office, 1957.
[14]	ERICSSON L E, REDING J P. Asymmetric vortex shedding from bodies of revolution[J]. Progress in Astronautics and Aeronautics, Tactical Missile Aerodynamics, 1986,104:243-296.
[15]	夏明, 李栋, 宋笔锋, 等. 细长旋成体大迎角非定常运动数值研究[J]. 航空计算技术, 2011, 41(3):1-5.
	XIA M, LI D, SONG B F, et al. Numerical simulation on unsteady motion of slender body at high angle of attack[J]. Aeronautical Computing Technique, 2011, 41(3):1-5. (in Chinese)
[16]	KUMAR R, GUHA T K, KUMAR R. Role of secondary shear-layer vortices in the development of flow asymmetry on a cone-cylinder body at high angles of incidence[J]. Experiments in Fluids, 2020, 61(10):1-20. doi: 10.1007/s00348-019-2836-9
[17]	QI Z Y, WANG Y K, BAI H L, et al. Effects of micro-perturbations on the asymmetric vortices over a blunt-nose slender body at a high angle of attack[J]. European Journal Mechanics/B Fluids, 2018,68:211-218.
[18]	QI Z Y, WANG Y K, WANG L, et al. Investigation on asymmetric flow over a blunt-nose slender body at high angle of attack[J]. Fluid Dynamics Research, 2017, 49(6):065508. doi: 10.1088/1873-7005/aa9582 URL
[19]	QI Z Y, ZONG S Y, WANG Y K, et al. Sources of asymmetric flow over the blunt-nose slender body[J]. European Journal of Mechanics/B Fluids, 2019, 75:372-399.
[20]	MENG X S, LONG Y X, WANG J L, et al. Dynamics and control of the vortex flow behind a slender conical forebody by a pair of plasma actuators[J]. Physics of Fluids, 2018, 30:024101. doi: 10.1063/1.5005514 URL
[21]	唐海敏, 杜厦, 傅建明, 等. 超声速细长体飞行器前置小翼展开过程的非定常特性[J]. 航空学报, 2018, 39(5):121701. doi: 10.7527/S1000-6893.2017.21701
	TANG H M, DU S, FU J M, et al. Unsteady performance of a supersonic slender vehicle during spreading of the front wings[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(5):121701. (in Chinese) doi: 10.7527/S1000-6893.2017.21701
[22]	彭程, 郭洋. 细长体自旋与锥动耦合运动作用下的流动结构研究[J]. 兵工学报, 2018, 39(3):519-527. doi: 10.3969/j.issn.1000-1093.2018.03.014
	PENG C, GUO Y. Research on flow field structure of slender spinning missile under coupling of conical and spinning motions[J]. Acta Armamentarii, 2018, 39(3):519-527. (in Chinese) doi: 10.3969/j.issn.1000-1093.2018.03.014
[23]	雷娟棉, 高毅, 勇政. 旋转导弹横向喷流干扰特性数值模拟[J]. 兵工学报, 2024, 45(1):105-121. doi: 10.12382/bgxb.2022.0379
	LEI J M, GAO Y, YONG Z. Numerical investigation of the jet interference characteristics of a lateral-jet-controlled spinning missile[J]. Acta Armamentarii, 2024, 45(1):105-121. (in Chinese) doi: 10.12382/bgxb.2022.0379
[24]	ERICSSON L E, REDING J P. Aerodynamics effects of asymmetric vortex shedding from slender bodies[R]. Reston, VA,US:AIAA, 1985.