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展弦比等于2的45°后掠机翼分别在0.6米× 0.6米低速槽壁风洞和2.25米直径低速开口风洞中进行了压力分布实验。在低速槽壁风洞中的实验有:在驻室高度为100毫米、槽壁全扩开角为0.4°的实验条件下, 进行了开闭比(试验段的槽壁开面积与总面积之比)分别为0,5.76%,10.08%,15.84%,20.16%和30.24%的实验; 在驻室高度为150毫米, 槽壁全扩开角为0.4°的实验条件下, 进行了开闭比为5.76%和10.08%的实验; 同时, 在驻室高度为100毫米,槽壁全扩开角为0.4°的实验条件下, 进行了开闭比为15.84%, 槽条数为8的实验。实验攻角范围均为-16°～+16°, 间隔为2°。实验风速为50米/秒, 以根弦弦长为参考长度的雷诺数为0.8×10~6。文中给出不同开闭比下的剖面和机翼的升力系数, 俯仰力矩系数和压差阻力系数随攻角变化的曲线, 并与2.25米直径低速开口风洞实验结果进行了比较。此外还给出了两种驻室高度和两种槽条数的实验结果。实验结果比较表明, 低速开槽试验段对洞壁干扰有显著影响。在本实验条件(风洞、模型)下, 在开闭比为10.08%～15.84%时,除翼尖部分局部地不成功外, 均消除了升力、阻力和俯仰力矩的洞壁干扰。结果比较还表明, 当开闭比为5.76%时,洞壁干扰随驻室高度的增加而略有增加, 当开闭比为10.08%时, 驻室高度的增加对洞壁干扰的影响甚小, 可以忽略不计。开闭比为15.84%时, 洞壁干扰随槽条数减少而稍有增加, 但其量也甚微,可以不计。
The 45 ° swept airfoil with an aspect ratio of 2 was used to conduct pressure distribution experiments in a 0.6m × 0.6m low velocity slot wind tunnel and a 2.25m diameter low velocity open wind tunnel respectively. Experiments in the low velocity slot wind tunnel show that the opening and closing ratio (the wall area of the test section and the total area of the test section) in the experimental conditions of a chamber height of 100 mm and a full expansion angle of the groove wall of 0.4 ° Ratio of 0,5.76%, 10.08%, 15.84%, 20.16% and 30.24%, respectively. Under the experimental conditions of a height of 150 mm and a full expansion angle of 0.4% 5.76% and 10.08%. At the same time, the opening and closing ratio of 15.84% and the number of slots of 8 were tested under the conditions of a height of 100 mm in the chamber and a full expansion angle of 0.4%. The range of experimental angle of attack is -16 ° ~ + 16 °, the interval is 2 °. The experimental wind speed was 50 m / s, and the Reynolds number with the length of the root chord as the reference length was 0.8 × 10 ~ 6. The curves of lift coefficient, pitch moment coefficient and drag coefficient of airfoil with angle of attack under different opening / closing ratios are given and compared with the experimental results of 2.25 m diameter low speed open wind tunnel. In addition, two kinds of experimental results of the height of the chamber and the number of two slots are given. The comparison of the experimental results shows that the low-speed slotted section has a significant influence on the interference of the wall. Under the experimental conditions (wind tunnel, model), when the open-close ratio is 10.08% ~ 15.84%, except the wingtip partially unsuccessful, the interference of lift, drag and pitching moment on the wall are eliminated. The results also show that when the opening-closing ratio is 5.76%, the wall-wall interference slightly increases with the increase of the height of the chamber. When the opening-closing ratio is 10.08%, the increase of the height of the chamber has little effect on the interference of the wall , Can be ignored. Open-close ratio of 15.84%, the wall of the interference with the slot number decreases slightly increased, but its amount is also very small, you can not count.