Vacuum mode debugging and flow field performance calibration of large-scale hypersonic wind tunnel
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摘要: 未来先进飞行器飞行高度不断增大，对风洞试验模拟能力的要求不断提高，需要高超声速风洞具备更低真空的运行能力，常规多级引射系统已不能完全满足要求。为提高风洞试验高度模拟范围，中国航天空气动力技术研究院（CAAA）在新建Φ1.2 m高超声速风洞基础上设计专用真空排气支路，实现了风洞压力真空模式运行。风洞系统调试及校测结果表明：经能力提升改造后，风洞各分系统工作正常且均达到性能设计指标，实现了马赫数5～8、高度40 km以上的高空低雷诺数高超声速试验条件模拟能力，试验段均匀区流场指标满足GJB 4399-2002高超声速风洞气动力试验的相关要求，为高空条件下飞行器气动特性及复杂高超声速流动问题的研究提供了试验平台。Abstract: With the continuous increase of the flight altitude of advanced aircraft in the future, the requirements for wind tunnel test simulation ability are constantly increasing, such as the lower vacuum running ability. The conventional multistage ejection system can no longer fully meet the operation requirements. In order to improve the height simulation range of the wind tunnel test, CAAA designed a vacuum exhaust branch based on the original equipment of its newly built Ф1.2 m hypersonic wind tunnel to realize the pressure vacuum mode operation of the wind tunnel. The wind tunnel system debugging and testing results show that after the wind tunnel capacity is improved, each subsystem works normally and the system performance reaches the design target, and the hypersonic flow field condition at the altitude above 40 km with Mach number 5–8 is realized. The flow field index in the uniform area of the test section meets the relevant requirements of the aerodynamic test of the National military standard GJB 4399-2002. It provides a test platform for the study of aerodynamic characteristics of aircraft and complex hypersonic flow at high altitude.
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图 2 总压十字排架测点分布示意
Figure 2. Distribution of measuring points of total pressure cross rake
图 4 不同马赫数总温调节曲线
Figure 4. Adjustment curve of total temperature of different Mach numbers
图 5 调压阀理论计算性能曲线与试验结果对比
Figure 5. Comparison test results with theoretical calculation performan-ce curves of pressure regulating valve
图 7 Ma=6喷管pt=0.297 MPa流场纹影
Figure 7. Schlieren flow field of Ma 6 nozzle at pt=0.297 MPa
图 8 Ma=6喷管pt=0.061 MPa流场纹影
Figure 8. Schlieren flow field of Ma=6 nozzle at pt=0.061 MPa
图 9 pt=0.297MPa、x=0截面马赫数分布曲线
Figure 9. Ma distribution curve of x=0 section at pt=0.297 MPa
图 10 pt=0.061 MPa、x=0截面马赫数分布曲线
Figure 10. Ma distribution curve of x=0 section at pt=0.061 MPa
图 11 试验段均匀区轴向截面平均马赫数分布
Figure 11. Average Ma distribution of axial section in test uniform area
图 12 能力提升改造后雷诺数与飞行模拟高度的扩展范围
Figure 12. The expanded Reynolds number and flight altitude after the capability improved
表 1 风洞压力真空模式运行参数（Ma=6）
Table 1. Wind tunnel running parameters of vacuum mode（Ma=6）
马赫数Ma Ma=6 前室总压pt/MPa 0.300 0.061 前室总温Tt/K 412 377 喷管出口静压p/Pa 188 39 模拟高度H/km 43 56 单位雷诺数Re/m–1 3.3×106 7.8×105 真空球罐初始压力ps/Pa <50 <50 
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表 2 Ma=6喷管压力真空模式流场性能
Table 2. Flow field performance results of Ma 6 nozzle
Ma pt/MPa Tt/K $ \overline {Ma} $ $|\Delta M{a_\infty }{|_{\max }} $ σ dMa/dx D0/mm 6 0.297 422 5.94 0.032 0.014 0.0072 900 0.061 390 5.84 0.045 0.018 –0.0015 840
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