Abstract Investigations of the temperature and heat flux distributions over the external surface of flying vehicles are important for the development of hypersonic planes. For obtaining correct results, experiments are performed in short-duration high-enthalpy wind tunnels. Determination of the stagnation temperature of the flow in such facilities is a challenging task due to short start-up times and high flow temperature. In this paper a new method is proposed for determining the stagnation temperature of a gas flow in the short-duration aerodynamic wind tunnels with stepwise changes in its parameters. The method is based on using two identical thermocouples with different initial temperatures. It is shown that in the case of jump-like changes in flow parameters the instrument function of the difference of the thermocouple readings coincides with the instrument function of each thermocouple, and the instrument function itself is actually the normalized temperature difference. The instrument function obtained in the study allows temperature retrieval by the method of deconvolution. This approach is highly sensitive to random noise of experimental data; therefore, regularization methods are applied for high-frequency noise suppression. A procedure for choosing the regularization parameter for temperature reconstruction is proposed. The research novelty of the article is that the proposed method allows exact reproduction of the stepwise function and instrument function without any additional assumptions, while the measurements and dynamic calibration are performed in one experiment. Applicability of the method for obtaining the stagnation temperature in the short-duration high-enthrall wind tunnel IT-302 M ITAM SB RUS is demonstrated.

中文翻译：

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短时气动设施中两根相同热电偶法测量气流滞止温度

摘要 飞行器外表面温度和热通量分布的研究对于高超音速飞机的发展非常重要。为了获得正确的结果，在短期高焓风洞中进行了实验。由于启动时间短和流动温度高，确定此类设施中流动的停滞温度是一项具有挑战性的任务。在本文中，提出了一种新方法，用于确定气流在其参数逐步变化的短时气动风洞中的停滞温度。该方法基于使用具有不同初始温度的两个相同热电偶。结果表明，在流量参数出现跳跃式变化的情况下，热电偶读数差的仪表函数与每个热电偶的仪表函数重合，仪表函数本身实际上是归一化的温差。研究中获得的仪器功能允许通过反卷积方法进行温度反演。这种方法对实验数据的随机噪声高度敏感；因此，正则化方法适用于高频噪声抑制。提出了一种为温度重建选择正则化参数的程序。文章的研究新颖之处在于所提出的方法可以准确再现逐步函数和仪器函数，而无需任何额外的假设，而测量和动态校准在一个实验中进行。证明了在短时高吸力风洞 IT-302 M ITAM SB RUS 中获得停滞温度的方法的适用性。