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对中国空气动力研究与发展中心马赫数为5左右的球锥模型在首次航天模型飞行试验中的温度测量数据进行了分析,通过辨识获得热流分布,发现飞行试验的测热数据后处理方法与地面风洞试验有很大差别,必须考虑温度变化历史,并考虑测温单元与周围飞行器壳体的三维传热才能得到正确的热流结果。采用工程计算方法对模型表面热流分布进行了计算,通过与飞行试验测量结果对比分析,发现测温点在发射上升段由湍流完全变为层流和在再入下降段由层流向湍流转捩具有不同的转捩准则数,边界层转捩存在滞后现象;根据地面风洞试验拟合出的转捩准则受到风洞噪声等因素的影响,预测的转捩位置比实际情况靠前;对于球钝锥外形,当x/R>50时,流场和热流趋于锥形流结果。本次模型飞行试验还首次验证了气动热工程方法对于马赫数小于5情况的适应性。
The temperature measurement data of the first aerospace model flight test was analyzed for the spherical cone model with a Mach number of about 5 at the China Aerodynamics Research and Development Center. By identifying the distribution of the heat flux, it was found that the thermal data post-processing method of the flight test and the ground Wind tunnel tests vary widely, and the history of temperature changes must be taken into account and the correct heat flow results can be obtained by considering the three-dimensional heat transfer between the temperature measurement unit and the surrounding aircraft shell. The heat flow distribution on the surface of the model was calculated by engineering calculation. Comparing with the measurement results of flight test, it was found that the temperature measurement point changed from turbulence to laminar flow in the ascending stage and from laminar to turbulent flow in the descending section. The number of different transitions lags behind the transition of the boundary layer. According to the wind tunnel test, the criterion of transition fitted by the wind tunnel test is influenced by wind tunnel noise and other factors, and the predicted transition position is higher than the actual situation. For the ball blunt Cone shape, when x / R> 50, the flow field and heat flow tend to conical flow results. This model flight test also validates, for the first time, the applicability of aerodynamic thermal engineering to Mach numbers less than five.