【摘要】 为了降低超声速客机进气道的声爆强度，设计了一种采用0°内唇罩角与发散等熵压缩设计的二元低声爆超声速进气道，并用边界层抽吸流动控制提高进气道气动性能。通过数值模拟的方法，研究了进气道重要设计参数对其气动性能与流动特性的影响，并探究了进气道对飞行器整体声爆特性的影响。结果表明：对于巡航马赫数1.8的超声速客机，低声爆进气道的高气动性能依赖于抽吸流动控制，控制效果与总压缩角、抽吸槽结构等因素有关；在设计状态下，低声爆进气道总压恢复系数可达0.956，声爆特性相比常规二元外压式进气道减小74%；常规进气道使飞机的近场声爆强度增大136%，而安装低声爆进气道的整机声爆特性在此基础上降低了4.5%。更多还原

【Abstract】 In order to reduce the sonic boom of a supersonic passenger aircraft inlet,a rectangular low-boom supersonic inlet was designed with features of internal 0° cowl and relaxed isentropic compression, boundary layer bleed was applied to enhance the aerodynamic performance of the inlet.Through numerical simulation methods,the influences of critical inlet design parameters on aerodynamic performance and flow characteristics were studied, and the effect of inlet on boom characteristics of aircraft was also investigated. The results showed that,for a supersonic passenger cruising at Mach number 1.8,the optimal performance of the low-boom inlet counted on the bleed control,which was determined by factors such as total compression angle and bleed slot structure; at design point,the total pressure recovery coefficient of low-boom inlet achieved 0.956,the boom signature was reduced by 74% compared with conventional rectangular external compression inlet; the conventional inlet increased the boom signature of the aircraft by 136%,while the boom signature of the aircraft with low-boom inlet decreased by 4.5% on the basis of conventional one.更多还原