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
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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

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图 2 计算网格

Figure 2. Computational grids

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图 3 无/有底部凹腔外形示意图

Figure 3. No/with bottom cavity profile diagram

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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

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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

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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

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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

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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

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图 9 不同开孔直径的底部凹腔

Figure 9. Bottom cavity with different hole diameters

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图 10 阻力系数随孔径的变化曲线

Figure 10. Curve of drag coefficient with hole diameter

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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

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图 12 孔倾斜角定义

Figure 12. Definition of hole inclination angle

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图 13 不同开孔倾斜角的底部凹腔

Figure 13. Bottom cavity with different hole inclination angles

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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

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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

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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

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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

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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

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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

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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

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图 21 不同开孔周向位置的底部凹腔

Figure 21. Bottom cavity with different hole circumferential positions

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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

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图 23 不同开孔数量的底部凹腔

Figure 23. Bottom cavity with different hole numbers

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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

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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）

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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