不同攻角下高超声速二元进气道性能研究

Performance study of hypersonic two-dimensional inlets with different attack angles

针对高超声速二维混压进气道,以最大总压恢复系数为目标,基于多楔面内收缩段设计原理,利用多楔角方法设计内收缩段长度和出口高度等。通过比较不同攻角下二元进气道总压恢复系数、流场及启动情况等多方面特性,验证了改变攻角对进气道启动特性改善的效果。

For two-dimensional mixed-compression hypersonic inlet,the internal compression section length and exit height were designed with the multi-ramp angle method to achieve the maximal recover coefficient according to the design theory of multi-wedge surface internal compression section.By comparing the total pressure recover coefficients,flow field and starting characteristics of two-dimensional inlets with different attack angles,the effect of changing attack angle on the improvement of inlet starting characteristics was validated.