宽域吻切乘波体参数敏感性分析与优化设计

袁熠祺; 李永洲; 杨学良; 孙迪; 罗喜胜; 张堃元

doi:10.13224/j.cnki.jasp.20240804

宽域吻切乘波体参数敏感性分析与优化设计

doi: 10.13224/j.cnki.jasp.20240804

袁熠祺^{1, 2,},
李永洲^{1, 2,*, ,},
杨学良^{1, 2},
孙迪^{1, 2},
罗喜胜³,
张堃元⁴

1.
南昌航空大学航空宇航学院，南昌 330063
2.
南昌航空大学新型航空飞行器江西省重点实验室，南昌 330063
3.
中国科学院力学研究所，北京 100190
4.
南京航空航天大学能源与动力学院，南京 210016

基金项目: 江西省双千计划创新领军人才项目（CK202206068）；航空科学基金（20240012056001）；国家重点实验室基金（6142701210102）

详细信息

作者简介:
袁熠祺（2000-），男，硕士，前体进气道一体化设计。E-mail：17879567200@163.com

通讯作者:
李永洲（1984-），男，教授，博士，高超声速推进技术。E-mail：nuaa-2004@126.com

中图分类号: V221.3
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- 被引次数: 0
出版历程
- 收稿日期: 2024-11-26
- 网络出版日期: 2026-06-25

Sensitivity analysis of parameters and optimal design of wide range osculating cone waverider

Yuan Yiqi^{1, 2
,},
Li Yongzhou^{1, 2,*
, ,},
Yang Xueliang^{1, 2},
Sun Di^{1, 2},
Luo Xisheng³,
Zhang Kunyuan⁴

1.
School of Aeronautics and Astronautics，Nanchang Hangkong University，Nanchang 330063，China
2.
Jiangxi Key Laboratory for Innovative Configuration Aircraft Design，Nanchang Hangkong University，Nanchang 330063，China
3.
Institute of Mechanics，Chinese Academy of Sciences，Beijing 100190，China
4.
College of Energy and Power Engineering，Nanjing University of Aeronauties and Astronautics，Nanjing 210016，China

摘要

摘要:
为了提升吻切锥乘波体宽域性能，选取前缘曲线函数系数a和l、激波型线函数系数b和c以及基准流场的半锥角δ_c共5个参数作为设计变量，在Ma=4～7范围内开展设计参数的敏感性分析，并采用第二代非支配排序遗传算法以容积率、设计点Ma=6和非设计点Ma=4升阻比为目标变量进行优化研究。结果表明：设计参数与总体性能参数之间存在显著的非线性关系，其中基准流场的半锥角对乘波体几何和气动性能起着决定性作用。相对基准构型，优化乘波体的容积率提升了7.1%，设计点Ma=6和非设计点Ma=4的升阻比分别提升了3.4%和10.7%。在宽马赫数范围内优化乘波体表现出较高的气动效率和较低总压损失，Ma=7时升阻比为4.88，即使前缘钝化后升阻比仍可保持在3.90。优化设计显著提升了乘波体设计点和非设计点的气动性能，具有良好的宽域适应性。
- 吻切乘波体 /
- 敏感性分析 /
- 多目标优化 /
- 宽马赫数 /
- 气动性能
Abstract:
The osculating cone waverider is studied in order to improve its wide area performance, five parameters, including the leading edge curve function coefficients a and l, shock wave curve function coefficients b and c, and the semi-cone Angle δ_c of the reference flow field, were selected as the design variables, and the sensitivity analysis of the design parameters was carried out in the range of Ma=4～7. The second generation of non-dominated sorting genetic algorithm is used to optimize the volume ratio, design point Ma6 and non-design point Ma=4 lift-drag ratio as the target variables. The results show a significant nonlinear relationship between the design parameters and the performance parameters, wherein the semi-cone angle of the reference flow field plays a crucial role in determining both the geometric and aerodynamic performance of the waverider. Compared with the reference model, the volume ratio of the optimized waverider is increased by 7.1%. At the design point of Ma=6 and the non-design point of Ma=4, the lift-drag ratio is increased by 3.4% and 10.7%. The optimized waverider over a wide Mach number range shows higher aerodynamic efficiency and lower total pressure loss, with a lift to drag ratio of 4.88 at Ma=7, which can be maintained at 3.90 even after leading edge bluntness. The optimized design significantly enhances the aerodynamic performance of both the design and non-design points of the waverider, and possesses good wide range adaptability.
- osculating cone waverider /
- sensitivity analysis /
- multi-objective optimization /
- wide Mach number range /
- aerodynamic performance

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图 1 吻切乘波体底面型线示意图

Figure 1. Curve of osculating cone waverider in the exit plane

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图 2 基准吻切锥乘波体轴测图

Figure 2. Axonometry of the reference osculating cone waverider

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图 3 不同网格数量下时对称面与下表面沿程静压分布Fig.3 Static pressure distribution of the symmetrical surface and the lower surface under different mesh sizes

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图 4 空天飞机模型三维视图

Figure 4. Three dimensional view of space plane model

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图 5 空天飞机表面及纵向对称面网格

Figure 5. Grids of the surface and longitudinal symmetry planes of aerospace plane

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图 6 0°攻角数值计算与实验纹影对比图

Figure 6. Comparison between numerical calculation and experimental schlieren of 0° angle of attack

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图 7 数值计算结果与风洞实验结果对比

Figure 7. Comparison between numerical calculation results and wind tunnel experimental data

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图 8 设计参数对容积率η影响图

Figure 8. Effect of design parameters on η

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图 9 设计点Ma=6设计参数对升阻比L/D影响图

Figure 9. Effect of design parameters on L/D at Ma=6

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图 10 非设计点Ma=4设计参数对升阻比L/D影响图

Figure 10. Effect of design parameters on L/D at Ma=4

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图 11 设计点Ma=6设计参数对俯仰力矩系数C_M影响图

Figure 11. Effect of design parameters on C_M at Ma=6

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图 12 设计点Ma=6时设计参数对总压恢复系数σ影响图

Figure 12. Effect of design parameters on σ at Ma=6

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图 13 三目标优化设计的 Pareto 前沿

Figure 13. Pareto front of the three objectives optimization

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图 14 多目标优化吻切锥乘波体构型

Figure 14. Multi-objective optimized osculating cone waverider

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图 15 不同来流马赫数时乘波体基准构型和优化构型的性能变化曲线

Figure 15. Performance variation curves between reference configuration and optimized configuration of waverider with different inflow Mach numbers

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图 16 钝化前后乘波体WR2的底面马赫数等值图

Figure 16. Contour of the bottom Mach number of the waverider WR2 before and after bluntness

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表 1 不同飞行马赫数下来流条件

Table 1. Incoming flow conditions at different flight Mach numbers

Ma	H/km	T₀/K	p₀/Pa	ρ₀/（kg/m³）
4	20	216.7	5529.3	8.9×10⁻²
5	23	219.5	3466.9	5.5×10⁻²
6	25	221.8	2549.2	4.0×10⁻²
7	27	223.5	1880.0	2.9×10⁻²

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表 2 乘波体基准设计参数

Table 2. Reference design parameters of waverider

δ_c	l	a	b	c
8.5	0.40	0.275	0.45	-0.59

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表 3 不同网格尺寸计算结果

Table 3. Calculation results of different mesh size

网格尺寸	C_L	C_D	C_M
粗网格	0.04845	0.009899	0.03111
中等网格	0.04849	0.009811	0.03118
密网格	0.04852	0.009814	0.03120

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表 4 风洞实验来流条件

Table 4. Wind tunnel experiment incoming flow conditions

Ma	Re	T₀/K	p₀/MPa	α/（°）
4.96	3.1×10⁷	376	1.5	−5～25

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表 5 设计参数取值区间

Table 5. Design parameters value range

δ_c	l	a	b	c
（7, 19）	（0.4, 0.7）	（0.2, 0.4）	（0.4, 0.6）	（−0.7, −0.5）

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表 6 R²方法的设计参数误差

Table 6. Design parameter error of R² method

参数	η	（L/D）₆	（L/D）₄
误差	0.975	0.985	0.990

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表 7 多目标优化的乘波体设计参数取值

Table 7. Design parameters values of multi-objective optimization waverider

δ_c	l	a	b	c
8.16	0.58	0.328	0.49	−0.58

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表 8 不同来流马赫数时钝化前后乘波体性能参数

Table 8. Performance parameters of waverider before and after bluntness at different incoming Mach numbers

Ma	R_c/mm	L/D	C_L	C_D	C_M	σ
4	0	5.90	0.059	0.010	0.037	0.97
4	3	4.54	0.059	0.013	0.038	0.96
5	0	5.47	0.052	0.0095	0.032	0.95
5	3	4.33	0.052	0.012	0.033	0.94
6	0	5.17	0.046	0.0089	0.029	0.92
6	3	4.09	0.045	0.011	0.029	0.90
7	0	4.88	0.041	0.0084	0.027	0.88
7	3	3.90	0.039	0.010	0.026	0.86

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