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在南航NH-1三音速风洞进行了NACA0012翼型跨音速风洞实验,讨论了洞壁开闭比和模型尺寸对驻室参考点静压、翼型表面压力分布的影响。结果表明,开闭比和模型尺寸对驻室静压有明显的影响,开闭比对翼型表面压力分布有很大影响。在α=0°时,超临界流动条件下,开闭比从6变到0.5,翼型上表面激波位置向后移动范围达20％的弦长,开闭比为4时,翼型接近于无堵塞干扰。当α=1°和M_∞=0.759时。消除洞壁干扰的最佳开闭比为4。
The NACA0012 airfoil wind tunnel experiment was carried out at China Southern NH-1 tristimulus wind tunnel. The effects of wall opening and closing ratio and model size on static reference pressure and airfoil surface pressure distribution were discussed. The results show that the open-close ratio and the model size have significant effects on the static pressure in the chamber, and the open-close ratio has a great influence on the airfoil surface pressure distribution. At α = 0 °, the opening-and-closing ratio changes from 6 to 0.5 at the supercritical flow conditions, and the chord length of 20% In the non-jamming interference. When α = 1 ° and M_∞ = 0.759. The best opening and closing ratio to eliminate the wall interference is 4.