连续式跨声速风洞压力损失计算研究

李庆利; 孟凡民; 李兴龙; 张刃; 崔晓春

doi:10.11729/syltlx20190139

连续式跨声速风洞压力损失计算研究

中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室, 沈阳 110034

详细信息

作者简介:
李庆利(1984-), 男, 河北秦皇岛人, 硕士研究生。研究方向:风洞设计与风洞试验技术研究。通信地址:沈阳市701信箱(110034)。E-mail:liqingli68@163.com

通讯作者:
孟凡民 E-mail: moonnuaa@126.com

中图分类号: V211.74
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- 文章访问数: 329
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出版历程
- 收稿日期: 2019-10-23
- 修回日期: 2019-12-22
- 刊出日期: 2020-12-24

Research on the calculation of pressure loss in continuous transonic wind tunnel

Aero Science Key Laboratory of High Reynolds Aerodynamic Force at High Speed, China Aerodynamics Research Institute of Aeronautics, Shenyang 110034, China

摘要

摘要: 为满足未来先进航空航天型号的发展需求，我国逐步展开了大型跨声速风洞建设工作；由于过去从未开展过大型连续式跨声速风洞建设，建设经验较为有限。连续式风洞压力损失估算及各部段气动参数计算是风洞结构、测控系统和动力系统设计的输入条件；压力损失估算结果的准确性，直接影响了风洞动力系统设计的难度。本文结合经典的压力损失计算方法，针对损失的关键部位，结合CFD数值模拟及缩比部段试验结果进行全面的分析，给出了特殊部段尤其是试验段的损失系数，并通过多次迭代计算的方式，给出了各部段气动性能。最后，将风洞压力损失估算值与某0.6 m量级连续式跨声速风洞试验结果进行对比，估算偏差在7.5%以内。
- 连续式风洞 /
- 跨声速 /
- 压力损失 /
- 试验验证
Abstract: In order to meet the demand of the development of advanced aerospace models in the future, the construction of large-scale transonic wind tunnels has been carried out. Since the construction of large-scale continuous transonic wind tunnels has never been carried out in the past, construction experience is limited. The estimation pressure loss of the continuous wind tunnel and the calculation of aerodynamic parameters of various parts are the design input conditions for the wind tunnel structure system, measurement and control system, and power system. The accuracy of pressure loss estimation results directly affects the difficulty of the wind tunnel power system design. Using the classical pressure loss calculation method combined with the CFD numerical simulation, this paper comprehensively analyzes the key parts of the loss and the results of scaled section test, and gives the loss coefficient of the special section, especially that of the test section, more accurately. The iterative calculation method gives the aerodynamic performance of each section accurately. Finally, by comparing the estimated value of the wind tunnel pressure loss with the test results of 0.6 m continuous wind tunnel, the estimated uncertainty is within 7.5%.
- continuous wind tunnel /
- transonic /
- pressure loss /
- experimental verification

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图 1 FL-61风洞布局图

Fig. 1 The FL-61 wind tunnel layout

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图 2 TCT风洞高速扩散段压缩性修正对损失的影响^[5]

Fig. 2 Effect of high-speed diffuser compression modification on loss of TCT wind tunnel^[5]

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图 3 TCT风洞压比估算值和测量值的对比^[5]

Fig. 3 Comparison of estimated and measured pressure loss in TCT wind tunnel^[5]

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图 4 槽壁试验段示意图

Fig. 4 The slotted test section

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图 5 槽壁试验段网格

Fig. 5 Mesh of the slotted test section

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图 6 试验段主要压力损失

Fig. 6 Main pressure loss in the test section

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图 7 Flap片关闭状态下计算结果

Fig. 7 The calculated results in flap off state

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图 8 不同喷管和试验段Ma数下抽气量^[7]

Fig. 8 The suction mass at different nozzles and different Mach numbers^[7]

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图 9 孔壁试验段简化模型(二维)CFD计算结果

Fig. 9 Calculation results of the simplified model (2D) for perforated-wall test section

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图 10 Ma=1.00，0.2 m试验段试验结果

Fig. 10 The test results of 0.2 m test section at Ma=1.00

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图 11 孔壁试验段不同试验车次试验结果

Fig. 11 The test results of perforated-wall test section

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图 12 0.2 m试验段试验结果(Ma=1.10)

Fig. 12 The test results of 0.2 m test section at Ma=1.10

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图 13 低超声速范围支架段马赫数云图

Fig. 13 Mach number diagram of model support section with low supersonic range

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图 14 模型支架段马赫数云图

Fig. 14 Mach number diagram of the model support section

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图 15 风洞参数计算流程图

Fig. 15 Flow chart of wind tunnel parameter calculation

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图 16 国际同类风洞设计的估算结果^[5]

Fig. 16 Estimation results of similar international wind tunnel^[5]

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图 17 估算与试验结果对比

Fig. 17 Comparison of estimation and the test results

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表 1 边界条件一览表

Table 1 List of boundary conditions

部件名称	边界条件
二维喷管入口	总温、总压、流动方向等
试验段出口	外插
风洞横向中间截面	对称面
计算模型半模分界面	对称面
单槽分界面	欧拉壁面
槽腔壁板	无滑移绝热壁
驻室壁面	无滑移绝热壁
试验段壁板	无滑移绝热壁
二维喷管壁板	无滑移绝热壁
Flap片	无滑移绝热壁

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表 2 风洞各部段损失系数

Table 2 Loss coefficient of each part of the wind tunnel

部段名称	当地损失系数	部段名称	当地损失系数
第二喉道段	0.0341	大角度扩散段	1.692
再入段	0.0078	风洞冷却器	20
方变圆段	0.018	大角度收缩段	0.05
第一扩散段	0.06	第三拐角段	0.25
第一拐角段	0.24	三、四拐角间等直段	0.012
一、二拐角间等直段	0.8452	第四拐角段	0.25
第二拐角段	0.24	稳定段	4.5
压缩机段	0.25	收缩段	0.34
第二扩散段	0.0685	喷管段	0.028

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表 3 不同压力损失计算方法不确定度汇总^[4]

Table 3 Accuracy of different pressure loss calculation methods^[4]

Uncertainty of circuit loss predictions
Project	Method	Loss estimation	Uncertainty
Facility upgr.	Analytical	Data base sim. tunnels	30%~40%
Facility upgr.	Semi-emp.	Experimental data base	< 5%~10%
New tunnel	Experiment	Test-rig high-speed leg	< 10%~15%
New tunnel	Experiment	Complete model tunnel	< 5%~10%
New tunnel	Semi-emp.	Loss program + test data	< 5%~10%
New tunnel	Semi-emp.	Data base sim. tunnels	30%~40%
New tunnel	Analytical	Present 1D method	< 10%~15%
New tunnel	Analytical	Numerical(CFD)

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