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内收缩基准流场的设计直接决定了内收缩进气道的最终性能。利用既有的特征线法型面生成程序,根据型面曲线方程,设计三种典型的不同升压规律的进气道型面,分别为压力梯度单调递增曲线、压力梯度单调递减曲线和等压力梯度曲线。以来流马赫数6.0为设计点,得到三种典型的内收缩基准流场,利用FLUENT商业软件对三种基准流场的二维模型进行分析和性能对比。分析发现,压力梯度单调递增流场的总压恢复系数最高,喉道截面以及隔离段的流场均匀性最好,但是等效内收缩比(前缘激波在中心体上的反射点所在的截面面积与喉道面积之比)过高,低马赫数起动性能不佳;压力梯度单调递减流场的性能与前者相反;综合考虑得出,等压力梯度流场的性能适中,是适合宽马赫数工作范围的较佳选择。通过三种基准流场的分析,为内收缩进气道的型面设计提供了依据。
The design of the internal shrinkage reference flow field directly determines the final performance of the internal shrinkage intake. According to the profile curve equation, three typical inlet profiles with different pressure increasing regularities are designed by using the existing characteristic line profiled surface generation program. They are the monotonically increasing pressure gradient curve, the monotone decreasing curve of pressure gradient and the equal pressure Gradient curve. Since the flow Mach number 6.0 is the design point, three typical internal contraction reference flow fields are obtained. The two-dimensional models of the three reference flow fields are analyzed and compared using FLUENT commercial software. The analysis shows that the monotonically increasing pressure gradient has the highest total pressure recovery coefficient, and the throat section and isolation section have the best uniformity of flow field. However, the equivalent internal shrinkage ratio (where the reflection point of the front shock wave is on the center body) Sectional area and throat area ratio) is too high, low Mach number starting performance is poor; pressure gradient monotonously decreasing flow field performance contrary to the former; comprehensive consideration that the equal pressure gradient flow field performance is moderate, is suitable for wide Mach Number of working range of the better choice. Through the analysis of three kinds of reference flow field, it provides the basis for the profile design of the inner shrinkage inlet.