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本文搭建了用于测定圆柱、翼型表面换热系数的实验平台。首先测定了圆柱在不同雷诺数下表面的换热系数值,以圆柱的迎风点为0°,其表面换热系数在0°~75°范围内随着角度的增大而减小。换热系数随雷诺数和测量点位置的变化趋势与文献中的结果是一致,本文搭建的实验台和采用的实验方法可以准确测量风洞中模型表面的换热系数。然后,用该试验装置测定了翼型水滴撞击区域表面的换热系数,并与数值模拟计算结果进行比较。数值计算能定性反映风洞中模型表面换热系数的变化趋势,可以为确定热气防冰的热负荷提供依据。
In this paper, an experimental platform for measuring the surface heat transfer coefficient of cylinder and airfoil was built. Firstly, the heat transfer coefficient of the cylinder under different Reynolds numbers was measured, and the windward point of the cylinder was 0 °. The surface heat transfer coefficient decreased with the increase of the angle within the range of 0 ° ~ 75 °. The trend of the heat transfer coefficient with the Reynolds number and the location of the measuring point is consistent with the results in the literature. The experimental bench and the experimental method adopted in this paper can accurately measure the heat transfer coefficient of the model surface in the wind tunnel. Then, the heat transfer coefficient of the surface of airfoil droplet impact zone was measured by the test device and compared with the numerical simulation results. Numerical calculation can qualitatively reflect the trend of the surface heat transfer coefficient in the wind tunnel, which can provide the basis for determining the thermal load of hot gas anti-icing.