关键词: 无隔道超声速进气道, Bump进气道, 进气道设计, 超声速流, 一体化设计, 计算流体力学, 风洞

Abstract: A side-mounted diverterless supersonic inlet (Bump inlet) is designed and the external and internal flow fields of the integral inlet/forebody are calculated. The Mach number contours and the pressure distribution of the flow fields are presented. Two lips with different inclination angles are designed and their effect on bypassing the boundary layer is compared. Furthermore, the flow characteristics between the Bump inlet and the ramp inlet with diverter are presented. Wind tunnel tests of the ramp inlet and Bump inlet models are conducted. The computational results with different model scales and inflow conditions (wind tunnel/flight conditions) are compared with experimental data, which showed good agreement. It can be concluded that the Bump inlet has better aerodynamic performance than the ramp inlet, and that the lip with two inclination angles can enhance the effect of bypassing the boundary layer. It is also discovered that the total pressure recovery of inlet calculated by flight condition is higher than that calculated by wind tunnel condition by 0.02-0.03.

Key words: diverterless supersonic inlet, Bump inlet, inlet design, supersonic flow, integrated design, computational fluid dynamics, wind tunnel