Ice accumulation on aircraft wings can cause a loss in lift and increased drag. Since the formation of different phenomena like rivulets, water runback, and ice ridges is probable, a better understanding of the underlying physics of these complex phenomena is highly desired. Therefore, having an advanced experimental technique capable of quantifying and characterizing the amount of water or ice will be of high interest. In the present study, a novel Colour-Coded Point Projection (CCPP) method is proposed and used in experiments to investigate the rivulet and ice formation on Al and SH surfaces over a NACA 0012 airfoil with a heated leading edge in the icing wind tunnel. The thickness profiles of rivulets and accreted ice were measured successfully and the effect of heating area on the leading edge and type of the surface were captured. The results showed that the proposed method is a valuable tool for on-line ice/water thickness measurements in an icing wind tunnel.

飞机机翼上的冰积聚会导致升力损失并增加阻力。由于可能形成诸如小溪，水流失和冰脊之类的不同现象，因此迫切需要更好地了解这些复杂现象的基本物理原理。因此，具有能够量化和表征水或冰量的先进实验技术将是人们的高度关注。在本研究中，提出了一种新颖的颜色编码点投影（CCPP）方法，并在实验中用于研究结冰风洞中带有加热前缘的NACA 0012机翼在Al和SH表面上的小流子和冰形成。成功地测量了小溪和积冰的厚度分布，并记录了加热面积对前缘和表面类型的影响。