Ice accretion or icing is a well-known phenomenon that entails a risk for the correct functioning of an aircraft. One of the areas more vulnerable to icing is the air data measuring system. This paper studies the icing protection offered by a heating system installed inside a multi-hole probe. The problem is initially solved analytically, creating a tool that can be used in order to predict the heating performance depending on the flying conditions. Later, the performance of the real system is investigated with a heated five-hole probe prototype in a wind tunnel experiment. The measured results are compared with the predictions made by the analytical model. Last, the icing protection provided by the system is estimated with respect to flying altitude and speed. As a result, a prediction tool that can be used in order to make quick icing risk predictions for straight cylindrical probes is delivered. Furthermore, the study provides some understanding about how parameters like altitude and air speed affect the occurrence of ice accretion.

中文翻译：

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用于飞机应用的加热多孔探头的解析对流模型的发展

积冰或结冰是一种众所周知的现象，会给飞机的正常运行带来风险。更容易结冰的领域之一是空气数据测量系统。本文研究了安装在多孔探头内的加热系统提供的结冰保护。该问题最初是通过分析解决的，创建了一个可用于根据飞行条件预测加热性能的工具。随后，在风洞实验中使用加热的五孔探针原型研究了真实系统的性能。将测量结果与分析模型做出的预测进行比较。最后，根据飞行高度和速度估计系统提供的结冰保护。其结果，提供了一种预测工具，可用于对直圆柱探头进行快速结冰风险预测。此外，该研究提供了一些关于高度和空气速度等参数如何影响积冰发生的理解。