低雷诺数效应对0.6m连续式风洞性能影响

熊波; 程松; 罗新福; 周恩民

doi:10.11729/syltlx20160079

低雷诺数效应对0.6m连续式风洞性能影响

doi: 10.11729/syltlx20160079

中国空气动力研究与发展中心, 四川绵阳 621000

详细信息

通讯作者:
熊波(1980-),男,四川仁寿人,工程师。研究方向:风洞流场调试。通信地址:四川省绵阳市中国空气动力研究与发展中心(621000)。E-mail:6643807@qq.com

中图分类号: V211.74
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出版历程
- 收稿日期: 2016-05-16
- 修回日期: 2016-11-02
- 刊出日期: 2017-02-25

Effects of low Reynolds number on performance of 0.6m continuous wind tunnel

China Aerodynamics Research and Development Center, Miangyang Sichuan 621000, China

摘要

摘要: 风洞试验中通常采用降低运行总压的方法来扩大风洞雷诺数模拟的下边界。同常压试验相比，在低雷诺数条件下，风洞流场是否存在明显变化，风洞流场品质是否满足指标要求，直接影响风洞试验数据的精准度。为了研究低雷诺数效应对0.6m连续式跨声速风洞性能（包括轴流式压缩机性能、总压及马赫数控制精度、流场均匀性）的影响，调试人员在0.6m连续式跨声速风洞中开展了大量相关试验，本文在对试验结果进行整理、分析的基础上，给出了Re对风洞性能的影响。结果表明：（1）Re对压缩机性能、总压控制精度、马赫数控制精度、流场均匀性都有明显影响，当Re_c<5×10⁵（c=0.1√A）时，雷诺数效应明显，且Re越小，影响越大。（2）0.6m连续式跨声速风洞能够真实、准确反映Re对风洞流场性能和测力试验数据的影响规律，是开展高空低雷诺数飞行器、翼型、发动机等性能研究的理想地面模拟试验平台。
- 雷诺数 /
- 压缩机 /
- 连续式风洞 /
- 流场性能
Abstract: In the wind tunnel tests, the method of decreasing stagnation pressure is usually adopted to expand the simulation scope of Reynolds number. Compared with the normal pressure test, in the low Reynolds number situation, the accuracy of the test data is directly affected by whether or not the change of the flow field is obviously and whether or not the quality of the flow field satisfies the index. In order to study the influence of Reynolds number on the 0.6m continuous wind tunnel performance, the relevant tests were carried out in the 0.6m continuous wind tunnel. Based on arrangement and analysis of the tests data, the results were given. It shows that: (1) The Reynolds number has obvious effect on the performance of the compressor, stagnation pressure control precision, Mach number control precision, the flow uniformity etc. When Re_c<5×10⁵(c=0.1√A is the cross-sectional area of the test section),the effect of Reynolds number on the performance of wind tunnel is obvious. The smaller the Reynolds number is, the greater the effect is. (2) The 0.6m continuous wind tunnel can accuratly manifest the influence law of the effects of Reynolds number on the flow field performance of the wind tunnel and the force test data. Therefore, it is a good test platform for the capability research on aircraft, airfoil, engine, etc., at low Reynolds number.
- Reynolds number /
- compressor /
- continuous wind tunnel /
- flow field performance

HTML全文

图 1 0.6m连续式跨声速风洞轮廓图

Figure 1. Sketch of the 0.6m continuous wind tunnel

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图 2 轴流式压缩机

Figure 2. Picture of the axial flow compressor

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图 3 离心式压缩机

Figure 3. Picture of the centrifugal compressor

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图 4 试验结果

Figure 4. Results of the tests

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图 5 不同Re翼型流线分布图

Figure 5. Streamline distribution of the airfoil flow at different Reynolds numbers

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图 6 理论计算结果

Figure 6. Theoretical calculation results

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图 7 Re对压比的影响

Figure 7. Effect of Reynolds number on the pressure ratio

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图 8 Re对损失系数的影响

Figure 8. Effect of Reynolds number on the coefficient of loss

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图 9 Re对压缩机出口总压系数分布均方根偏差的影响(c=0.1$\sqrt{A2}$)

Figure 9. Effect of Reynolds number on the standard deviation of the stagnation pressure coefficient in the compressor exit(c=0.1$\sqrt{A2}$)

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图 10 p₀=100kPa，速度分布

Figure 10. Velocity distribution (p₀=100kPa)

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图 11 p₀=20kPa，速度分布

Figure 11. Velocity distribution (p₀=20kPa)

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图 12 总压系数随时间变化曲线

Figure 12. The curves of coefficient of the stagnation pressure with time

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图 13 Re对总压控制精度影响曲线

Figure 13. The curves of effect of Reynolds number on the stagnation pressure control precision

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图 14 Re对马赫数控制精度影响曲线

Figure 14. The curves of effect of Reynolds number on the Mach number control precision

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图 15 Re对Ma均匀性的影响

Figure 15. Effect of Reynolds number on the Mach number uniformity

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图 16 Re对C_L^α的影响

Figure 16. Effect of Reynolds number on the C_L^α

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图 17 Re对C_D0的影响

Figure 17. Effect of Reynolds number on the C_D0

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图 18 Re对C_M^CL的影响

Figure 18. Effect of Reynolds number on the C_{_M^CL}

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表 1 流场校测结果(p₀=20kPa)

Table 1. The results of the flow field calibration(p₀=20kPa)

Ma	平均总压/kPa	总压控制精度	Ma 控制精度	模型区均方根偏差
0.2	20.0756	0.07%	0.0030	0.0019
0.3	20.0507	0.08%	0.0024	0.0015
0.4	20.0508	0.07%	0.0016	0.0015
0.5	20.0510	0.10%	0.0015	0.0013
0.6	20.0481	0.08%	0.0018	0.0013
0.7	20.0754	0.07%	0.0010	0.0016
0.8	20.0926	0.10%	0.0014	0.0018
0.9	20.0501	0.08%	0.0014	0.0021
1.0	20.0373	0.08%	0.0011	0.0027
1.1	20.0407	0.10%	0.0009	0.0090
1.2	20.0832	0.09%	0.0013	0.0110
1.3	20.0964	0.09%	0.0018	0.0078
1.4	20.0500	0.10%	0.0010	0.0104

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