Design and construction progress of AVIC Φ1.0 m hypersonic wind tunnel
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摘要: 航空工业1 m量级高超声速风洞（FL-64）是国内最新建设的一座暂冲自由射流式大口径常规高超声速风洞，采用吹引式运行方式，同时考虑到低动压试验需要，另建有真空抽气系统。详细介绍了FL-64风洞的总体性能指标、关键部段设计、流场校测和标模试验结果。风洞性能指标如下：模拟马赫数范围4.0～8.0；总压范围0.1～8.0 MPa；总温范围300～900 K；单位雷诺数范围3.3×106～4.6×107 m–1；有效运行时间不小于30 s。FL-64风洞与航空工业亚跨超三声速风洞（FL-60）可形成高低马赫数搭配，涵盖马赫数0.3～8.0的宽速域高超声速飞行器试验需求，特别是马赫数4.0的总焓模拟能力可与真实飞行条件匹配，为我国高马赫数飞行器研制提供有效的气动试验平台。Abstract: The 1 m hypersonic wind tunnel for the AVIC （FL-64） is the newly built blow down free jet type large-diameter conventional hypersonic wind tunnel in China. It adopts the blowing type operation mode, at the same time, considering the test requirements of low dynamic pressure, a vacuum exhaust system is also equipped. The overall performance, key component design, flow field calibration and preliminary standard model test results of the FL-64 wind tunnel are presented in detail. The performance of the wind tunnel are as follows: the range of Mach number: 4.0 – 8.0; the total pressure range of the settling chamber: 0.1 – 8.0 MPa; the total temperature range of the settling chamber: 300 – 900 K; the unit Reynolds number range: 3.3×106 – 4.6×107 m–1; the effective operating time is not less than 30 s. The FL-64 wind tunnel combined the FL-60 trisonic （Subsonic, Transonic, Supersonic） wind tunnel forming the high and low Mach number range, this can cover the wide-speed range aircraft test with a Mach number of 0.3 – 8.0. Especially the duplication capability of the total enthalpy of Mach number 4.0 can match the real flight conditions. Overall, the successful completion of the FL-64 wind tunnel provide an effective test platform for the development of nation’s high Mach number aircraft.
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Key words:
- hypersonic /
- large-scale wind tunnel /
- aerodynamic test /
- wind tunnel design /
- flow field calibration
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图 1 FL-64风洞总体布局轮廓图
1. 加热器 2. 高温高压截止阀 3. 稳定段 4. 喷管 5. 试验段 6. 真空支路 7. 两级引射系统 8. 消音塔
Figure 1. General layout of FL-64 wind tunnel
图 3 两级调压系统二级阀的特性曲线
Figure 3. Characteristic curve of secondary pressure regulating valves
图 6 Ma=6.0引射器对称面压力和马赫数云图
Figure 6. Ma=6.0 Pressure and Mach number contour of ejector symmetry plane
图 8 Ma=5.0喷管出口不同截面马赫数分布
Figure 8. Mach number distribution of different sections at Ma=5.0 nozzle outlet
图 13 标模试验数据准确度对比验证曲线
Figure 13. Comparison and verification curve of accuracy of test data
表 1 世界主要1 m量级常规高超声速气动力风洞
Table 1. The 1 m conventional hypersonic aerodynamic wind tunnel in the world
风洞 所属
机构尺寸 Ma 总压
/MPa总温
/K加热
形式Tunnel A AEDC 1.00 m ×1.00 m 1.5～5.5 Tunnel B AEDC Φ1.27 m 6.0,8.0 0.140～5.800 388～750 电加热 Tunnel C AEDC Φ1.27 m 10.0,12.0 0.400～13.600 916～1250 电加热 Tunnel 9 AEDC Φ1.50 m 7.0,10.0～16.0 19.200 2028 T-116 TsAGI 1.00 m ×1.00 m 1.8～10.0 1075 电加热 Φ1.27 m JAXA Φ1.27 m 10.0 1.000～10.000 600～1200 卵石床 S4MA ONERA Φ1.00 m（0.67 m） 6.0,10.0,12.0 0.300～4.100 500～1843 卵石床 FD-20A CARDC Φ1.00 m 4.0～10.0 上限约12.000 上限约1100 电蓄热 FD-16 CAAA Φ1.20 m 5.0～10.0 0.074～10.000 350～1068 燃烧蓄热 FL-64 AVIC ARI Φ1.00 m 4.0～8.0 0.100～8.000 300～900 电蓄热 
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表 2 FL-64风洞Ma=5.0流场校测结果
Table 2. Flow field calibration results of Ma=5.0
x/mm 50 195 340 485 630 所有截面
的平均值$\overline {Ma} $ 5.047 5.055 5.048 5.051 5.048 5.050 $|\Delta M{a_{{\infty _{\max }}}}| $ 0.038 0.026 0.029 0.029 0.029 0.030 ${\sigma _{M{a_\infty }}} $ 0.0095 0.0087 0.0111 0.0107 0.0115 0.0103 $\dfrac{ {|\Delta M{a_{ {\infty _{\max } } } }|} }{ {M{a_\infty } } }$ 0.81% 0.52% 0.59% 0.58% 0.57% 0.61%
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表 3 FL-64风洞Ma=6.0流场校测结果
Table 3. Flow field calibration results of Ma=6.0
x/mm 50 195 340 485 630 所有截面
的平均值$\overline {Ma} $ 6.035 6.031 6.035 6.039 6.036 6.036 $ |\Delta M{a_{ {\infty _{\max } } } }| $ 0.059 0.032 0.030 0.034 0.037 0.039 ${\sigma _{M{a_\infty } } } $ 0.0132 0.0105 0.0113 0.0134 0.0116 0.0120 $\dfrac{ {|\Delta M{a_{ {\infty _{\max } } } }|} }{ {M{a_\infty } } } $ 0.98% 0.53% 0.50% 0.57% 0.62% 0.64%
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