| Citation: | XU Yin, LI Bo, JIANG Dongchen. Design method and performance of low-boom supersonic inlet[J]. Journal of Aerospace Power, 2025, 40（6）：20230798 doi: 10.13224/j.cnki.jasp.20230798
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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.
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