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针对高超声速内收缩进气道,以有旋特征线理论研究了一种型面压升规律可控的新型轴对称基准流场;结合流线追踪技术,以等压力梯度为例,探讨了一种圆形进口的内收缩进气道设计方法,并对三种不同压升规律的内收缩进气道性能进行了比较.结果表明,采用基准流场的内收缩进气道,能较好地保持基准流场的预定压升规律,从而拓宽了基准流场的选择范围,提高了型面设计的灵活性.针对所研究的三种压升规律,压力梯度逐渐增大的进气道其压缩效率最高,等压力梯度次之,压力梯度逐渐减小的进气道压缩效率最低.此外,研究发现,通过调整压升规律还可改变进气道的内外压分配,有助于实现此类进气道的宽马赫数范围工作.
A new type of axisymmetric reference flow field with controllable pressure rise is studied using the theory of spin-line characteristic for the hypersonic contraction of the inlet. Based on the streamline tracing technique, taking equal pressure gradient as an example, The results show that using the internal contraction inlet of the reference flow field can be better Which can broaden the range of reference flow field and improve the flexibility of profile design.According to the three pressure rise laws studied, the pressure gradient gradually increases and the compression of its inlet The efficiency is the highest, the pressure gradient is the second, and the pressure gradient is gradually reduced, the efficiency of the inlet compression is the lowest.In addition, the study found that by adjusting the pressure rise law can also change the internal and external pressure distribution of the inlet, Airway wide Mach range work.