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为便于前缘钝化高超声速进气道设计与性能分析,将CFD方法与特征线法相结合,提出一种高超声速钝化锥/楔流场的快速精确计算方法 (CCM方法)。该方法将CFD方法的精度与特征线方法的效率相结合,可进行前缘钝化高超声速进气道的快速设计与性能分析。利用CCM方法设计了一种前缘钝化两级锥轴对称进气道构型,分析了前缘钝化对进气道前体波系位置的影响,并采用CFD模拟开展了相应的对比考察和性能参数影响研究。结果表明,对于轴对称进气道,当前缘钝化半径较小时,进气道前体波系位置及流动性能基本不变;当钝化半径增至一定的尺度后,前缘激波向外偏移以及进气道性能参数的下降开始显露并渐趋明显。在设计状态点附近,低来流Ma下前缘钝化对轴对称进气道性能影响更为显著。对于该轴对称进气道构型,前缘钝化半径在10%捕获半径内变化时,进气道流量系数、出口截面总压恢复系数等参数变化幅度均在10%以内;进气道自起动Ma数略有下降。
In order to facilitate the design and performance analysis of the leading-edge passivated hypersonic inlet, a fast and accurate method (CCM method) for the hypersonic passivation cone / wedge flow field was proposed by combining the CFD method with the characteristic line method. The method combines the accuracy of the CFD method with the efficiency of the feature line method to enable rapid design and performance analysis of the leading-edge passivated hypersonic inlet. The CCM method is used to design a two-stage cone-shaped asymmetric intake duct with leading-edge passivation. The influence of leading-edge passivation on the position of intake duct precursors is analyzed. Corresponding contrastive studies are carried out by CFD simulation And the impact of performance parameters. The results show that when the passivation radius is small, the position and the flow performance of the inlet precursor wave are basically unchanged for the axisymmetric inlet. When the passivation radius increases to a certain extent, the front shock wave is outward Offset and intake port performance parameters began to decline and become apparent. In the vicinity of the design state point, the influence of the leading edge passivation at lower flow Ma on the axisymmetric inlet characteristics is more pronounced. For this axisymmetric inlet configuration, when the leading edge passivation radius changes within 10% of the capture radius, the variation range of inlet flow coefficient and outlet section total pressure recovery coefficient are within 10% Starting Ma slightly decreased.