Experimental research of special perforated wall test section for transonic wind tunnel
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摘要: 为满足型号试验需求，2.4 m×2.4 m跨声速风洞需在不改变现有洞体结构和安装条件下新研制一个截面尺寸为3 m×1.92 m（宽×高）的专用开孔壁试验段。为了降低技术风险和投资风险，以0.24 m×0.20 m跨声速风洞（2.4 m×2.4 m跨声速风洞的引导风洞）为实验平台，采用变截面气动设计方案新设计、加工了一个专用开孔壁试验段实验件，并开展了预先性实验研究工作。通过实验研究验证了专用开孔壁试验段气动设计方案可行，且试验段模型区内流场达到设计指标要求。实验还考察了壁板扩开角、主流引射缝开度、开孔率分布等参数对流场均匀性的影响，研究结果表明：在扩开角0.3°、引射缝开度12 mm、加速区采用递增方式开孔时，专用开孔壁试验段的流场能够满足马赫数均方根偏差σM≤0.01（0.4≤Ma＜1.0）、σM≤0.02（1.0≤Ma≤1.2、1.4）设计指标要求，并且在Ma≤1.0时，σM达到了国军标合格指标要求。研究工作为2.4 m×2.4 m跨声速风洞专用开孔壁试验段设计提供了技术支持，也为该风洞下一阶段调试和流场校测提供了可供参考的调试参数。Abstract: The perforated test section of the 2.4 m×2.4 m injection driven transonic wind tunnel is redesigned so as to study the aerodynamic force of advanced aircraft. A scaled experimental research of the special perforated wall test section is conducted in the 0.24 m×0.20 m transonic wind tunnel (the pilot wind tunnel of the 2.4 m×2.4 m transonic wind tunnel). The experimental study has demonstrated that the project is feasible, and the flow quality of the flow field in the special perforated wall test section reaches the required specification. Influences of the diffuse angle in the test section, the open width of the mainstream ejected slot and the porosity of the perforated wall are also investigated. The results have been used to design the perforated test section of the 2.4 m×2.4 m transonic wind tunnel. The calibration parameters for the future perforated test section flow field calibration in this tunnel are also provided.
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Key words:
- transonic wind tunnel /
- test section /
- perforated /
- experimental research /
- aerodynamics design
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图 4 不同引射缝开度时试验段马赫数均方根偏差对比曲线
Figure 4. Root-mean-square error of Mach number for different open heights of the mainstream eject slot
图 5 不同扩开角时试验段马赫数均方根偏差对比曲线
Figure 5. Root-mean-square error of Mach number for different diffuser angles in the test section
图 6 不同前过渡段形式时试验段马赫数均方根偏差对比曲线
Figure 6. Root-mean-square error of Mach number for different porosities in the transition section
图 7 不同中段加速区形式时试验段马赫数均方根偏差对比曲线
Figure 7. Root-mean-square error of Mach number for different porosities in the entrance test section
图 8 各马赫数下轴向马赫数的分布曲线
Figure 8. Axial Mach number distribution curves for different Mach numbers in the test section
图 9 不同开车参数下试验段轴向马赫数对比曲线
Figure 9. Axial Mach number distribution curves for different operation parameters
表 1 不同组合参数下实验状态
Table 1. Test conditions of different parameters
α/(°) h/mm γ/(°) 前过渡段形式 中段加速区形式 0 12 33.7 不开孔 全开孔 0 18 23.2 不开孔 全开孔 0.5 12 23.2 不开孔 全开孔 0.5 12 23.2 左右壁开孔 全开孔 0.5 12 23.2 上下壁开孔 全开孔 0.5 12 23.2 四壁开孔 全开孔 0.3 12 26.7 不开孔 全开孔 0.3 12 26.7 不开孔 贴孔 
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表 2 各马赫数下实验结果
Table 2. Experimental results with different Mach numbers
Ma参 Ma核 σM dMa/dx 0.41 0.41 0.0022 0.0102 0.49 0.49 0.0028 0.0120 0.61 0.61 0.0037 0.0185 0.70 0.70 0.0043 0.0209 0.79 0.79 0.0034 0.0099 0.89 0.89 0.0029 -0.0040 0.94 0.94 0.0042 -0.0144 0.99 1.00 0.0069 -0.0248 1.05 1.05 0.0150 -0.0691 1.10 1.10 0.0131 0.0484 1.20 1.23 0.0200 -0.1430 1.38 1.42 0.0176 0.0598
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