| 高速风洞中条带悬挂支撑干扰研究 |
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| 引用本文： | 李强,刘大伟,陈德华.高速风洞中条带悬挂支撑干扰研究[J].实验流体力学,2017,31(1):100-108. |
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| 作者姓名： | 李强 刘大伟 陈德华 |
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| 作者单位： | 1.中国空气动力研究与发展中心 空气动力学国家重点实验室, 四川 绵阳 621000 |
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| 摘 要： | 以Ty-154标模为研究对象，分别对其有、无假条带干扰进行试验，获得了条带支撑干扰量。采用嵌套网格方法，数值模拟了条带对Ty-154标模的干扰作用。结合试验与数值结果，分析了支撑干扰产生的机理，探讨了条带支撑对模型局部细节的一些破坏可能产生的影响，并与尾、腹支撑干扰特点进行了对比。数值模拟与试验结果吻合较好，研究方法可靠性高。结果表明:条带支撑对CL干扰很小，使得CD增大约0.0005，并产生一个较小的抬头力矩干扰，较尾、腹支撑优势明显；Ma>0.9时，条带干扰量增大，干扰规律不定；动带机身开槽及定带转轴对试验结果影响都很小。
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| 关 键 词： | 条带支撑 支撑干扰 风洞试验 计算流体力学 嵌套网格 |
| 收稿时间： | 2016-03-26 |
Study on the support interference of vane suspension support system in high speed wind tunnels |
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| Affiliation: | 1.State Key Laboaratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China2.High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China |
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| Abstract: | Experiments with and without fake vanes are conducted using Ty-154 standard model, and the interference magnitudes are acquired. Chimera grids are used in numerical investigation. Through the work of experiments and CFD, the interference mechanisms are studied, the influence of model's breakage caused by the vanes is investigated, and the sting and belly blade support methods are also brought to compare with the vanes. The numerical results coincide well with experiments, proving the reliability of the study method. Due to the vanes' interference, the CD increase about 0.0005 and a small head-up pitching moment occurs while CL changes little. The vane support shows apparent advantages over sting and belly blade support in support interference characteristics. Under the Ma>0.9 condition, the vanes' interference increases and becomes unpredictable. The influence of the crack between the front vane and the fuselage as well as the shaft of back vane is small. |
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