高超声速气动热标模HyHERM-Ⅰ试验

doi:10.7527/S1000-6893.2022.27804

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高超声速气动热标模HyHERM-Ⅰ试验

胡守超, 庄宇(), 李贤, 江涛

中国空气动力研究与发展中心超高速空气动力研究所，绵阳 621000

收稿日期:2022-07-13 修回日期:2022-07-27 接受日期:2022-08-22 出版日期:2022-12-25 发布日期:2022-08-31
通讯作者: 庄宇 E-mail:y_zhuang1@163.com
基金资助:
国家数值风洞工程;国家自然科学基金(11902338)

Hypersonic aero-heating environment research model HyHERM-I: Experiment

Shouchao HU, Yu ZHUANG(), Xian LI, Tao JIANG

Hypervelocity Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang 621000，China

Received:2022-07-13 Revised:2022-07-27 Accepted:2022-08-22 Online:2022-12-25 Published:2022-08-31
Contact: Yu ZHUANG E-mail:y_zhuang1@163.com
Supported by:
National Numerical Wind Tunnel Project;National Natural Science Foundation of China(11902338)

摘要/Abstract

摘要：

为满足高超声速飞行器气动热环境预测与评估技术发展需要，开展了以地面试验数据为基础的高超声速气动热标模研制工作。标模试验涵盖了不同马赫数Ma（6，8，10，12）、雷诺数Re、总温T₀、前缘半径、攻角等，在Ma、Re模拟基础上，进行T₀模拟，并详细分析了流场参数的不确定度，Ma、Re、T₀、总压P₀不确定度分别优于±1%、±10%、±6%、 ±3%。设计了表征二维流动的“平板-双楔”气动热标模HyHERM-I，采用薄膜热电阻、热电偶传感器测量模型表面热流及边界流态，并结合高速纹影分析了分离区流动特点。试验结果表明：驻点热流重复性测量精度优于±5%。尖前缘、大压缩角下拐角分离区增大。尖前缘、高雷诺数、低马赫数状态下边界层流动更易转捩并发展为湍流，同时转捩和湍流可在一定程度上抑制流动分离并减小分离区。HyHERM-I气动热标模试验数据丰富、详实，可为数值方法验证与确认、试验技术验证、天地相关性分析以及高超声速飞行器设计等提供参考。

关键词: 高超声速气动热标模（HyHERM）, 激波风洞, 热流, 边界层, 流动分离

Abstract:

The ground test study on hypersonic aero-heating standard model has been carried out， so as to meet the needs of the development of hypersonic aero-heating environment prediction and evaluation. The test covers different Mach number （6， 8， 10， 12）， Reynolds number， total temperature， leading edge radius， and angle of attack. The uncertainty of flow field parameters is analyzed in detail. The uncertainty of Ma， Re， T₀ and P₀ is better than ±1%， ±10%， ±6%， ±3% respectively. A "plate-double wedge" test model HyHERM-I is designed， which characterize the two-dimensional hypersonic flow. The heat flux and boundary layer flow state is measured by thin film gauge or thermocouple， and the flow characteristics of the separation zone are analyzed with high-speed schlieren. The test results show that， the repeatability measurement accuracy of stagnation-point heat flux is better than ±5%. Smaller leading edge radius and larger compression angle results in a larger separation zone. The boundary layer flow is more likely to transition and develop into turbulence while smaller leading edge radius， larger Reynolds number， low Mach number. Besides， the flow separation is restrained by the transition and turbulence flow. The test data of HyHERM-I can be used as a reference for numerical verification and validation， testing technology validation， correlation study between flight and ground test， as well as for hypersonic vehicle design.

Key words: Hypersonic aero-Heating Environment Research Model (HyHERM), shock tunnel, heat flux, boundary-layer, flow separation

中图分类号:

V211

胡守超, 庄宇, 李贤, 江涛. 高超声速气动热标模HyHERM-Ⅰ试验[J]. 航空学报, 2022, 43(S2): 233-248.

Shouchao HU, Yu ZHUANG, Xian LI, Tao JIANG. Hypersonic aero-heating environment research model HyHERM-I: Experiment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 233-248.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

位置	编号	流向X/mm	法向Y/mm	展向Z/mm	测点数
前缘线	1	-217/-242	0	-120	1
	2	-217/-242	0	-80	1
	3	-217/-242	0	-40	1
	4	-217/-242	0	0	1
	5	-217/-242	0	40	1
	6	-217/-242	0	80	1
	7	-217/-242	0	120	1
平板	1	-190	×2	0	2
	2	-140	×2	0	2
	3	-90	×2	0	2
	4	-40	×2	0/±60	6
	5	-30	×2	0	2
	6	-20	×2	0	2
	7	-10	×2	0	2
	8	-6	×2	0	2
楔	9	6	×2	0/±60	6
	10	10	×2	0	2
	11	20	×2	0	2
	12	30	×2	0	2
	13	40	×2	0/±60	6
	14	60	×2	0	2
	15	80	×2	0	2
	16	100	×2	0	2
	17	120	×2	0	2
合计					53

参数		流场						偏差（不确定度）/%
参数		1	2	3	4	5	6	偏差（不确定度）/%
总温T₀/K		640	1 540	1 540	940	930	1 540	±6
总压P₀/MPa		2.14	7.37	11.12	3.85	22.59	17.17	±3
马赫数Ma		5.7	8.0	10.1	10.0	10.4	12.1	±1
单位雷诺数Re/m^-1		1.3×10⁷	4.0×10⁶	3.2×10⁶	3.1×10⁶	1.7×10⁷	3.1×10⁶	±10
静温T/K		86	121	78	46	42	55
静压P/Pa		1 841	659	214	88	397	98
密度ρ/（kg·m^-3）		7.20×10^-2	1.84×10^-2	9.24×10^-3	6.40×10^-3	3.16×10^-2	6.00×10^-3
自由流速度U/（m·s^-1）		1 079	1 792	1 817	1 385	1 379	1 830
驻点热流测量值/（W·cm^-2）		26.43	97.32	62.13	20.46	43.98	51.39	±5
F-R_Newton	计算值/（W·cm^-2）	25.27	88.74	63.83	19.16	41.64	51.75
F-R_Newton	与试验值偏差/%	4.39	8.82	-2.74	6.35	5.32	-0.70
F-R_Stokes	计算值/（W·cm^-2）	28.15	99.93	72.03	21.52	46.77	58.47
F-R_Stokes	与试验值偏差/%	-6.51	-2.68	-15.93	-5.18	-6.34	-13.78

序号	流场	攻角α/（º）	前缘半径R/mm	等效组合
1	1	0	5	Ⅱ Ⅲ
2	1	-15		Ⅳ Ⅰ
3	2	0		Ⅱ Ⅲ
4	2	-15		Ⅳ Ⅰ
5	3	0		Ⅱ Ⅲ
6	3	-15		Ⅳ Ⅰ
7	4	0		Ⅱ Ⅲ
8	4	-15		Ⅳ Ⅰ
9	5	0		Ⅱ Ⅲ
10	5	-15		Ⅳ Ⅰ
11	6	0		Ⅱ Ⅲ
12	6	-15		Ⅳ Ⅰ
13	3	0	1	Ⅱ Ⅲ
14	4	0		Ⅱ Ⅲ
15	5	0		Ⅱ Ⅲ

试验状态		分离点距拐角长度L_s/mm	再附点距拐角长度L_r/mm	分离激波角β_ss/（°）	主激波角β_ms/（°）
1	上表面	46	17	21.5	9.0
1	下表面	25	10	11.5	13.4
2	上表面	78	58	20.1
2	下表面	24	11	20.0	13.6
3	上表面	75	29	18.6	8.0
3	下表面	27	16	17.6	8.4
4	上表面	115	66	17.0
4	下表面	32	14	20.0	12.7
5	上表面	64	32	20.1	6.3
5	下表面	42	25	16.9	7.2
6	上表面	135	61	14.0
6	下表面	32	25	19.7
7	上表面	81	39	17.9	6.4
7	下表面	71	28	16.7	7.0
8	上表面	151	69	11.1
8	下表面	50	33	19.7
9	上表面	61	23	18.3	7.7
9	下表面	38	16	11.3	3.4
10	上表面	145	66	15.4
10	下表面	25	17	19.2	11.0
11	上表面	80	46	19.0	7.3
11	下表面	40	27	15.3	4.7
12	上表面	133	85	12.2
12	下表面	42	26	20.0
13	上表面	179	66	13.3
13	下表面	46	17	16.7	7.2
14	上表面	180	70	13.5
14	下表面	56	28	12.3	6.7
15	上表面	152	63	11.0
15	下表面	58	24	14.3	8.5

流场	半径R/mm	攻角α/（°）	流场前缘热流值/（W·cm^-2）							测量平均值/（W·cm^-2）	F-R_Newton		F-R_Stokes
流场	半径R/mm	攻角α/（°）	1	2	3	4	5	6	7	测量平均值/（W·cm^-2）	计算值/（W·cm^-2）	偏差/%	计算值/（W·cm^-2）	偏差/%
1	5	0	34.16	34.42	35.14	35.88	36.76	34.98	35.72	35.29	30.95	12	34.48	2
1		-15	34.06	36.19	34.07	38.30	36.71	36.52	33.32	35.60
2		0	125.46	118.06	120.47	121.02	119.29	125.24	120.65	121.46	108.68	11	122.39	-1
2		-15	124.38	115.77	116.75	121.04	114.58	124.23	123.38	120.02
3		0	74.25	72.10	73.14	74.11	74.66	76.45	74.23	74.13	78.18	-5	88.22	-19
3		-15	70.52	67.59	70.22	70.95	69.51	71.31	70.80	70.13
4		0	26.37	25.39	25.58	26.49	25.95	27.08	25.69	26.08	23.47	10	26.36	-1
4		-15	25.72	24.74	25.51	25.61	25.02	25.65	24.83	25.30
5		0	54.26	53.82	54.83	54.64	53.18	54.86	54.13	54.25	51.00	6	57.28	-6
5		-15	51.63	50.11	49.96	50.70	50.54	50.00	50.49	50.49
6		0	62.83	62.96	63.35	63.17	64.85	63.68	63.01	63.41	63.38	0	71.61	-13
6		-15	61.59	60.76	61.42	62.01	60.92	62.75	61.39	61.55
3	1	0	183.48	180.01	193.62	181.00	192.32	186.27		186.12	174.81	6	197.26	-6
4		0	62.85	59.13	69.34	69.10	69.10	64.21		65.62	52.47	20	58.93	10
5		0	130.65	127.90	141.69	144.47	145.50	133.89		137.35	114.04	17	128.08	7

高超声速气动热标模HyHERM-Ⅰ试验

Hypersonic aero-heating environment research model HyHERM-I: Experiment

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