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为了探究前体典型几何参数对高超声速前体/进气道气动特性的影响,在相同的前体外压缩角度和几何长度下,对基于圆锥截线参数控制横向截面的高超声速前体流动特性开展了三维数值模拟分析。采用控制变量法研究了高超声速前体宽度比、形状参数、形状角度参数以及水平半宽控制曲线次数对高超声速前体/进气道气动性能的影响。结果显示:上述四个几何参数对前体横向压力梯度的构建均产生一定的影响,导致前体横向溢流,进而影响前体/进气道的气动性能。增大前体宽度比、形状参数、水平半宽控制线次数,减小形状角度参数,可减小前体展向压力梯度及横向溢流,提高前体/进气道流量捕获特性,在本文研究范围内,上述参数变化对应的前体/进气道流量系数分别增加了25.1%,13.7%,20.3%及12.2%。
In order to explore the influence of typical geometric parameters of precursors on the aerodynamic characteristics of hypersonic precursors / inlets, the flow characteristics of hypersonic precursors based on cone-section parameters were studied under the same pre-compression angle and geometry length Three-dimensional numerical simulation analysis. The influence of hypersonic precursor width ratio, shape parameters, shape angle parameters and the number of horizontal half-width control curves on the aerodynamic performance of hypersonic precursors / inlets was investigated by the control variable method. The results show that the above four geometrical parameters all affect the construction of the lateral pressure gradient of the precursor, leading to the lateral overflow of the precursor and the influence of the aerodynamic performance of the precursor / inlet. Increasing the precursor width ratio, shape parameters, the number of horizontal and half width control lines, reducing the shape angle parameters can reduce the forward pressure gradient and lateral overflow of the precursor to improve the precursor / inlet flow trapping characteristics in this article Within the scope of the study, the precursor / inlet flow coefficient corresponding to these parameter changes increased by 25.1%, 13.7%, 20.3% and 12.2% respectively.