考虑附面层影响的二元混压式进气道设计

Design of a two-dimensional mixed-compression supersonic inlet with boundary layer consideration

采用等激波强度的方法,考虑附面层修正,设计了一种飞行马赫数Ma=3.0的二元混压式进气道.通过数值仿真,模拟了激波-边界层的相互影响,研究了附面层抽吸对内流场的影响,获得了进气道内部复杂的流场分布,以及不同背压下进气道的起动特性.计算表明所设计的进气道性能较好,附面层抽吸对稳定正激波有明显的作用,提高了进气道抗反压能力.给出的方法可用于二元混压式进气道的初步设计和验证.

Based on constant shock intensity method,a two-dimensional mixed-compression supersonic inlet was designed for flight at Mach number of 3.0.The correction was made for the effects of boundary layer.Quasi-one-dimensional analysis shows that the designed inlet has a good performance.By two-dimensional viscous simulation of inlet flows with terminal shocks,flow status of complicated flow field was presented in two-dimensional mixed-compression supersonic inlet.The reflections and intersections of various shock...