底部凹腔加侧开孔减阻研究

崔文瑶; 郭德春

doi:10.13224/j.cnki.jasp.20240307

底部凹腔加侧开孔减阻研究

doi: 10.13224/j.cnki.jasp.20240307

崔文瑶^{1, 2,},
郭德春^{1, 2,*, ,}

1.
北京空天技术研究所，北京 100074
2.
北京空天技术研究所空天飞行技术全国重点实验室，河北雄安 071700

详细信息

作者简介:
崔文瑶（1990-），女，高级工程师，博士，主要从事气动力设计研究。E-mail：18813122677@139.com

通讯作者:
郭德春（1984-），男，研究员，硕士，主要从事气动力设计研究。E-mail：paperwyspr@163.com

中图分类号: V423.6
计量
- 文章访问数: 1143
- HTML浏览量: 514
- PDF量: 44
- 被引次数: 0
出版历程
- 收稿日期: 2024-05-14
- 网络出版日期: 2025-11-27

Study on drag reduction of bottom cavity with side hole

CUI Wenyao^{1, 2
,},
GUO Dechun^{1, 2,*
, ,}

1.
Beijing Aerospace Technology Institute，Beijing 100074，China
2.
National Key Laboratory of Aerospace Flight Technology，Beijing Aerospace Technology Institute，Xiongan Hebei 071700，China

摘要

摘要:
为了研究高速来流下底部凹腔加侧开孔的减阻效果，采用数值计算对带有底部凹腔及侧开孔的旋成体进行了模拟。研究了侧开孔的孔径、孔倾斜角、开孔位置、开孔数量几个因素对减阻效果的影响规律。结果表明：孔径的影响规律非线性且存在最优解，随孔径增大，减阻效果先增强后减弱。孔倾斜角越小，减阻效果越差。开孔位置离凹腔底部越近，越有利于流动再附于底部，减阻效果越好。周向位置对减阻效果影响较小。开孔数量越多，本质上相当于总的开孔面积增大，减阻效果越差。由于进入开孔的流动仍为超声速，即使被小孔改变了流动方向，也仍然没有得到充分减速。在来流马赫数为6的情况下，底部凹腔加侧开孔的减阻效果存在一定的局限性。
- 减阻 /
- 高速 /
- 底部 /
- 凹腔 /
- 侧开孔
Abstract:
In order to study the drag reduction effect of bottom cavity with side hole under high speed free stream, numerical simulation was carried out for the spin-formed body with bottom cavity and side hole. The effects of hole diameter, hole inclination angle, hole position and hole number on drag reduction are studied. The results show that the effect of hole diameter is nonlinear and there is an optimal solution. With the increase of hole diameter, and drag reduction increases first and then decreases. The smaller the hole inclination angle, the worse the drag reduction effect. The closer the hole is to the bottom of the cavity, the more favorable it is for the flow to adhere to the bottom, and the better the drag reduction effect. The circumferential position of the hole has little effect on the drag reduction effect. The larger the number of holes is, the larger the total hole area is, and the worse the drag reduction effect is. Since the flow into the hole is still supersonic, even if the flow direction is changed by the hole, it is still not sufficiently decelerated. Under the free stream of Mach number 6, the drag reduction effect of bottom cavity with side hole has certain limitations.
- drag reduction /
- high speed /
- bottom /
- cavity /
- side hole

HTML

图 1 计算模型

Figure 1. Computational model

下载: 全尺寸图片幻灯片

图 2 计算网格

Figure 2. Computational grids

下载: 全尺寸图片幻灯片

图 3 无/有底部凹腔外形示意图

Figure 3. No/with bottom cavity profile diagram

下载: 全尺寸图片幻灯片

图 4 阻力和摩阻随飞行高度的变化曲线

Figure 4. Curve of drag and friction with flight height

下载: 全尺寸图片幻灯片

图 5 阻力和摩阻随马赫数的变化曲线

Figure 5. Curve of drag and friction with Mach number

下载: 全尺寸图片幻灯片

图 6 阻力和摩阻随攻角的变化曲线

Figure 6. Curve of drag and friction with angle of attack

下载: 全尺寸图片幻灯片

图 7 无凹腔与有凹腔不加侧开孔、有凹腔加侧开孔的三维流线及表面压力分布

Figure 7. Three dimensional flow line and surface pressure of non bottom cavity and bottom cavity without side hole and bottom cavity with side hole

下载: 全尺寸图片幻灯片

图 8 无凹腔与有凹腔不加侧开孔、有凹腔加侧开孔的对称面马赫数云图和二维流线

Figure 8. Mach number and two-dimensional streamlines of symmetric surfaces of non bottom cavity and bottom cavity without side hole and bottom cavity with side hole

下载: 全尺寸图片幻灯片

图 9 不同开孔直径的底部凹腔

Figure 9. Bottom cavity with different hole diameters

下载: 全尺寸图片幻灯片

图 10 阻力系数随孔径的变化曲线

Figure 10. Curve of drag coefficient with hole diameter

下载: 全尺寸图片幻灯片

图 11 不同开孔直径的对称面马赫数云图和流线

Figure 11. Mach number and streamlines of symmetric surfaces with different hole diameters

下载: 全尺寸图片幻灯片

图 12 孔倾斜角定义

Figure 12. Definition of hole inclination angle

下载: 全尺寸图片幻灯片

图 13 不同开孔倾斜角的底部凹腔

Figure 13. Bottom cavity with different hole inclination angles

下载: 全尺寸图片幻灯片

图 14 阻力系数随孔倾斜角的变化曲线

Figure 14. Curve of drag coefficient with hole inclination angle

下载: 全尺寸图片幻灯片

图 15 不同开孔倾斜角的对称面马赫数云图和流线

Figure 15. Mach number and streamlines of symmetric surfaces with different hole inclination angles

下载: 全尺寸图片幻灯片

图 16 不同开孔倾斜角底部中心线压力曲线

Figure 16. Bottom centerline pressure curve for different hole inclination angles

下载: 全尺寸图片幻灯片

图 17 不同开孔流向位置的底部凹腔

Figure 17. Bottom cavity with different hole positions on flow direction

下载: 全尺寸图片幻灯片

图 18 阻力系数随开孔位置的变化曲线

Figure 18. Curve of drag coefficient with hole positions

下载: 全尺寸图片幻灯片

图 19 不同开孔流向位置的对称面马赫数云图及表面压力

Figure 19. Mach number and streamlines of symmetric surfaces and surface pressure with different hole inclination angles

下载: 全尺寸图片幻灯片

图 20 不同开孔流向位置底部中心线压力曲线

Figure 20. Bottom centerline pressure curve for different hole positions on flow direction

下载: 全尺寸图片幻灯片

图 21 不同开孔周向位置的底部凹腔

Figure 21. Bottom cavity with different hole circumferential positions

下载: 全尺寸图片幻灯片

图 22 不同开孔周向位置的对称面马赫数云图和流线

Figure 22. Mach number and streamlines of symmetric surfaces with different hole circumferential positions

下载: 全尺寸图片幻灯片

图 23 不同开孔数量的底部凹腔

Figure 23. Bottom cavity with different hole numbers

下载: 全尺寸图片幻灯片

图 24 阻力系数随开孔数量的变化曲线

Figure 24. Curve of drag coefficient with hole numbers

下载: 全尺寸图片幻灯片

图 25 不同开孔数量表面压力及三维流线（流线用马赫数着色）

Figure 25. Surface pressure with different number of holes and three-dimensional streamlines （streamlines colored by Mach number）

下载: 全尺寸图片幻灯片

图 26 不同开孔数量底部中心线压力曲线

Figure 26. Bottom centerline pressure curve for different hole numbers

下载: 全尺寸图片幻灯片

表 1 来流条件

Table 1. Free stream condition

Ma	α/（°）	β/（°）	p_∞/Pa	T_∞/K	U_∞/（m/s）
6	0	0	12111.8	216.65	1770.02

下载: 导出CSV

表 2 网格无关性验证

Table 2. Grid independence verification

网格数	阻力系数C
1159101	0.064793655
1818576	0.064796465
2884286	0.064587351

下载: 导出CSV

表 3 飞行高度对阻力和摩阻的影响

Table 3. Effect of flight height on drag and friction

高度/km	马赫数	攻角	阻力系数C	摩阻系数f
5	6	0	0.061209	0.018834
15	6	0	0.064139	0.022170
25	6	0	0.070003	0.028516

下载: 导出CSV

表 4 马赫数对阻力和摩阻的影响

Table 4. Effect of Mach number on drag and friction

高度/km	马赫数	攻角	阻力系数C	摩阻系数f
15	5	0	0.078748	0.027485
15	6	0	0.064139	0.022170
15	7	0	0.054189	0.018367

下载: 导出CSV

表 5 攻角对阻力和摩阻的影响

Table 5. Effect of angle of attack on drag and friction

高度/km	马赫数	攻角	阻力系数C	摩阻系数f
15	6	0	0.064139	0.022170
15	6	4	0.080879	0.023282
15	6	8	0.133978	0.025888
15	6	12	0.237403	0.030520

下载: 导出CSV

表 6 不同开孔直径的减阻效果

Table 6. Rag reduction of different hole diameter

φ/mm	C	∆C/%	u/（m/s）	v/（m/s）	δ/（°）
0	0.064587
10	0.064431	−0.24	58.57	763.58	85.61
20	0.064423	−0.26	132.92	405.87	71.87
30	0.064171	−0.65	409.24	584.78	55.02
36	0.064139	−0.69	571.57	591.35	45.97
40	0.064167	−0.65	610.46	520.41	40.45
50	0.064589	0	619.59	417.07	33.95
60	0.065767	1.83	787.05	513.89	33.14

下载: 导出CSV

表 7 不同开孔倾斜角的减阻效果

Table 7. Rag reduction of different hole inclination angles

θ/（°）	C	∆C/%	u/（m/s）	v/（m/s）	δ/（°）
0	0.064587
30	0.064297	−0.45	768.31	478.66	31.92
50	0.064211	−0.58	750.96	512.18	34.29
70	0.064164	−0.66	621.75	580.23	43.02
90	0.064139	−0.69	571.57	591.35	45.97

下载: 导出CSV

表 8 不同开孔流向位置的减阻效果

Table 8. Rag reduction of different hole positions on flow direction

x/mm	∆C	C/%	涡核位置x/mm	涡核位置y/mm
0	0.064587
b	0.064097	−0.76	2.81279	0.062699
b+25	0.064139	−0.69	2.83739	0.046927
b+50	0.064354	−0.36	2.79967	−0.02857

下载: 导出CSV

表 9 不同开孔周向位置的减阻效果

Table 9. Rag reduction of different hole circumferential positions

周向位置	C	∆C/%	u/（m/s）	v/（m/s）	δ/（°）
0	0.064587
上	0.06417	−0.65	606.11	−735.46	−50.51
下	0.064139	−0.69	571.57	591.35	45.97

下载: 导出CSV

表 10 不同开孔数量的减阻效果

Table 10. Rag reduction of different hole numbers

开孔数量	C	∆C/%	C_k
0	0.064587
1	0.064097	−0.76	0.000338583
2	0.064114	−0.73	0.000660505
4	0.064197	−0.60	0.001362261

下载: 导出CSV

参考文献(21)

[1]	张帅. 高速飞行器防热减阻新概念构型的气动性能[J]. 航空动力学报, 2021, 36(11): 2292-2305. ZHANG Shuai. Aerodynamic performance of new conceptual configuration of high speed vehicle. s heat flux and drag reduction[J]. Journal of Aerospace Power, 2021, 36(11): 2292-2305. (in Chinese doi: 10.13224/j.cnki.jasp.20200477 ZHANG Shuai. Aerodynamic performance of new conceptual configuration of high speed vehicle. s heat flux and drag reduction[J]. Journal of Aerospace Power, 2021, 36(11): 2292-2305. (in Chinese) doi: 10.13224/j.cnki.jasp.20200477
[2]	张帅. 高速稀薄流域防热减阻概念构型气动性能[J]. 航空动力学报, 2022, 37(1): 124-141. ZHANG Shuai. Conceptual configuration aerodynamic performance of heat flux and drag reduction in high speed rarefied flow[J]. Journal of Aerospace Power, 2022, 37(1): 124-141. (in Chinese doi: 10.13224/j.cnki.jasp.20200541 ZHANG Shuai. Conceptual configuration aerodynamic performance of heat flux and drag reduction in high speed rarefied flow[J]. Journal of Aerospace Power, 2022, 37(1): 124-141. (in Chinese) doi: 10.13224/j.cnki.jasp.20200541
[3]	张帅, 郭建, 戴梧叶. 高速飞行器减阻杆槽道组合构型减阻防热特性研究[J]. 航空动力学报, 2023, 38(12): 3063-3072. ZHANG Shuai, GUO Jian, DAI Wuye. Investigation on drag and heat flux reduction induced by a novel combinational spike and channel concept for high speed vehicles[J]. Journal of Aerospace Power, 2023, 38(12): 3063-3072. (in Chinese ZHANG Shuai, GUO Jian, DAI Wuye. Investigation on drag and heat flux reduction induced by a novel combinational spike and channel concept for high speed vehicles[J]. Journal of Aerospace Power, 2023, 38(12): 3063-3072. (in Chinese)
[4]	张露, 李杰. 基于RANS/LES方法的超声速底部流场数值模拟[J]. 航空学报, 2017, 38(1): 120102. ZHANG Lu, LI Jie. Numerical simulations of supersonic base flow field based on RANS/LES approaches[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1): 120102. (in Chinese ZHANG Lu, LI Jie. Numerical simulations of supersonic base flow field based on RANS/LES approaches[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1): 120102. (in Chinese)
[5]	臧国才, 李树常. 弹箭空气动力学[M]. 北京: 兵器工业出版社, 1989.
[6]	卓长飞, 武晓松, 封锋. 超声速流动中底部排气形式对减阻性能的影响[J]. 航空学报, 2014, 35(8): 2144-2155. ZHUO Changfei, WU Xiaosong, FENG Feng. Effect of base bleed type on drag reduction performance in supersonic flow[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(8): 2144-2155. (in Chinese ZHUO Changfei, WU Xiaosong, FENG Feng. Effect of base bleed type on drag reduction performance in supersonic flow[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(8): 2144-2155. (in Chinese)
[7]	李彪, 王良明, 杨志伟. 底凹结构减阻效应数值分析[J]. 北京航空航天大学学报, 2022, 48(4): 682-690. LI Biao, WANG Liangming, YANG Zhiwei. Numerical analysis on drag reduction effect of base cavity[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(4): 682-690. (in Chinese doi: 10.13700/j.bh.1001-5965.2020.0623 LI Biao, WANG Liangming, YANG Zhiwei. Numerical analysis on drag reduction effect of base cavity[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(4): 682-690. (in Chinese) doi: 10.13700/j.bh.1001-5965.2020.0623
[8]	谷嘉锦. 底凹弹丸的风洞实验研究[J]. 南京航空航天大学学报, 1979, 11(1): 243-253. Gou Carkin. The study of wind tunnel experiments of a ball with hollow base[J]. Journal of Nanjing University of Aeronautics & Astronautics, 1979, 11(1): 243-253. (in Chinese Gou Carkin. The study of wind tunnel experiments of a ball with hollow base[J]. Journal of Nanjing University of Aeronautics & Astronautics, 1979, 11(1): 243-253. (in Chinese)
[9]	KRUISWYK R W, DUTTON J C. Effects of a base cavity on subsonic near-wake flow[J]. AIAA Journal, 1990, 28(11): 1885-1893. doi: 10.2514/3.10495
[10]	HERRIN J L, DUTTON J C. Supersonic base flow experiments in the near wake of a cylindrical afterbody[J]. AIAA Journal, 1994, 32(1): 77-83. doi: 10.2514/3.11953
[11]	CLEMENTS R R. Computer models of separated flows behind two dimensional bluff bodies[D]. Cambridge, East of England, UK: University of Cambridge, 1973.
[12]	MOLEZZI M J, DUTTON J C. Study of subsonic base cavity flowfield structure using particle image velocimetry[J]. AIAA Journal, 1995, 33(2): 201-209. doi: 10.2514/3.12390
[13]	KRUISWYK R, DUTTON J. An experimental investigation of the effects of a base cavity on thenear-wake flowfield of a body at subsonic and transonic speeds[C]//27th Aerospace Sciences Meeting. Reno, US: AIAA, 2013: 67-77.
[14]	陆海波, 颛孙世周, 孙凤文, 等. 不同形状底凹结构对火炮弹丸飞行阻力影响研究[J]. 弹箭与制导学报, 2016, 36(5): 112-114, 141. LU Haibo, ZHUANSUN Shizhou, SUN Fengwen, et al. Research on influence of base cavity with different shape on aerodynamic drag of projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2016, 36(5): 112-114, 141. (in Chinese doi: 10.15892/j.cnki.djzdxb.2016.05.029 LU Haibo, ZHUANSUN Shizhou, SUN Fengwen, et al. Research on influence of base cavity with different shape on aerodynamic drag of projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2016, 36(5): 112-114, 141. (in Chinese) doi: 10.15892/j.cnki.djzdxb.2016.05.029
[15]	陆海波, 崔国亮, 张海涛, 等. 火炮弹丸底凹结构流场仿真及其减阻机理分析[J]. 兵器装备工程学报, 2016, 37(9): 1-4, 31. LU Haibo, CUI Guoliang, ZHANG Haitao, et al. Flow field simulation and drag reducing mechanism analysis of projectile with base cavity[J]. Journal of Ordnance Equipment Engineering, 2016, 37(9): 1-4, 31. (in Chinese LU Haibo, CUI Guoliang, ZHANG Haitao, et al. Flow field simulation and drag reducing mechanism analysis of projectile with base cavity[J]. Journal of Ordnance Equipment Engineering, 2016, 37(9): 1-4, 31. (in Chinese)
[16]	陆海波, 高洁. 侧倾底凹结构对火炮弹丸阻力的影响[J]. 兵器装备工程学报, 2019, 40(6): 5-9. LU Haibo, GAO Jie. Research on shrinkage shape of base cavity upon aerodynamic drag of projectile[J]. Journal of Ordnance Equipment Engineering, 2019, 40(6): 5-9. (in Chinese LU Haibo, GAO Jie. Research on shrinkage shape of base cavity upon aerodynamic drag of projectile[J]. Journal of Ordnance Equipment Engineering, 2019, 40(6): 5-9. (in Chinese)
[17]	王中原. 底凹弹侧壁斜孔减小底阻分析[J]. 南京理工大学学报, 1997, 21(1): 17-20. WANG Zhongyuan. Analysis of base drag reduced by side holes in the projectile with base cavity[J]. Journal of Nanjing University of Science and Technology, 1997, 21(1): 17-20. (in Chinese doi: 10.14177/j.cnki.32-1397n.1997.01.005 WANG Zhongyuan. Analysis of base drag reduced by side holes in the projectile with base cavity[J]. Journal of Nanjing University of Science and Technology, 1997, 21(1): 17-20. (in Chinese) doi: 10.14177/j.cnki.32-1397n.1997.01.005
[18]	鞠玉涛, 周长省, 李坚. 底凹弹绕流流场波谱规律数值分析[J]. 弹箭与制导学报, 2003, 23(增刊4): 144-146. JU Yutao, ZHOU Changsheng, LI Jian. Numerical analysis of wave spectrum law of flow field around concave projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2003, 23(Suppl.4): 144-146. (in Chinese doi: 10.15892/j.cnki.djzdxb.2003.s4.012 JU Yutao, ZHOU Changsheng, LI Jian. Numerical analysis of wave spectrum law of flow field around concave projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2003, 23(Suppl.4): 144-146. (in Chinese) doi: 10.15892/j.cnki.djzdxb.2003.s4.012
[19]	王芳, 郎田, 魏志芳. 底凹装置对弹丸阻力系数的影响[J]. 兵工自动化, 2014, 33(11): 1-3, 13. WANG Fang, LANG Tian, WEI Zhifang. Effect of base cavity to projectile drag coefficient[J]. Ordnance Industry Automation, 2014, 33(11): 1-3, 13. (in Chinese WANG Fang, LANG Tian, WEI Zhifang. Effect of base cavity to projectile drag coefficient[J]. Ordnance Industry Automation, 2014, 33(11): 1-3, 13. (in Chinese)
[20]	朱安迪, 成佳敏, 陆毅, 等. 轨道炮高速动能射弹的底凹减阻特性研究[J]. 科技与创新, 2020(23): 32-34, 39. ZHU Andi, CHENG Jiamin, LU Yi, et al. Study on drag reduction characteristics of rail Gun high-speed kinetic energy projectile with concave bottom[J]. Science and Technology & Innovation, 2020(23): 32-34, 39. (in Chinese doi: 10.15913/j.cnki.kjycx.2020.23.012 ZHU Andi, CHENG Jiamin, LU Yi, et al. Study on drag reduction characteristics of rail Gun high-speed kinetic energy projectile with concave bottom[J]. Science and Technology & Innovation, 2020(23): 32-34, 39. (in Chinese) doi: 10.15913/j.cnki.kjycx.2020.23.012
[21]	轩海彬, 张文洁, 于勇, 等. 亚跨声速流动中底凹减阻的数值模拟[J]. 兵器装备工程学报, 2017, 38(11): 1-8. XUAN Haibin, ZHANG Wenjie, YU Yong, et al. Numerical study on drag reduction of projectile in subsonic and transonic speed[J]. Journal of Ordnance Equipment Engineering, 2017, 38(11): 1-8. (in Chinese XUAN Haibin, ZHANG Wenjie, YU Yong, et al. Numerical study on drag reduction of projectile in subsonic and transonic speed[J]. Journal of Ordnance Equipment Engineering, 2017, 38(11): 1-8. (in Chinese)