对一种典型布局背负式二元曲面压缩进气道不同攻角下的流动进行了数值仿真研究。结果显示：随着飞行攻角的增大，进气道的流量系数和喉道总压恢复系数同时下降，当攻角由0°增大到10°时，流量系数下降了24.4%，总压恢复系数下降了14.8%。边界层隔道可以有效提高进气道的流量系数和总压恢复系数，流量系数提升约4%，喉道总压恢复系数提升约0.02。研究分析表明，随着飞行攻角的增加，前体对背负进气道的遮挡效应诱导出现前体膨胀波，进而引起进气道进口前气流加速。进气道进口前马赫数较高且空间分布不均匀是导致流量系数和总压恢复系数同步下降的主要原因。据此，建立了此类背负式布局前体/进气道流量特性理论模型，揭示了进口前马赫数和飞行攻角的线性相关性，并可据此预测进气道的流量特性。通过改变进气口在前体沿流向的相对位置，可改善边界层对进气道内流的影响，提升流量系数和总压恢复系数，但由于进口前马赫数依然较高且分布不均匀，提升幅度有限。

Numerical simulations were conducted to investigate the flow of a typical layout of dorsal binary curved compression inlet at different angles of attack. The results show that the flow coefficient of the inlet and the total pressure recovery coefficient of the throat decrease simultaneously with the increase of the angle of attack, and the flow coefficient decreases by 24.4% and the total pressure recovery coefficient decreases by 14.8% when the angle of attack increases from 0° to 10°. The boundary layer diverter can effectively improve the flow coefficient and total pressure recovery coefficient of the inlet, in which the flow coefficient increased by about 4%, and the total pressure recovery coefficient of the throat increased by about 0.02. The analysis of the study shows that, with the increase of the angle of attack of the flight, the masking effect of the forebody on the dorsal inlet induces the appearance of the forebody expansion wave, which causes the acceleration of the airflow in front of the inlet. The higher Mach number and uneven distribution in front of the inlet are the main reasons for the simultaneous decrease of the flow coefficient and the total pressure recovery coefficient. Accordingly, a theoretical model of the flow characteristics of the forebody/inlet for this type of dorsal layout is established, which reveals the linear correlation between the Mach number in front of the inlet and the angle of attack, which can be used to predict the flow characteristics of the inlet accordingly. By changing the relative position of the inlet along the flow direction in the forebody, the influence of the boundary layer on the inlet flow can be improved, and the flow coefficient and total pressure recovery coefficient can be enhanced, but the enhancement is limited due to the fact that the Mach number in front of the inlet is still high and unevenly distributed.