考虑附面层影响的二元混压式进气道设计

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. 

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

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 waves inside the inlet and the separation flows induced by shock wave/boundary layer interaction were displayed reasonably.Boundary layer bleed was considered to minimize separation and provide uniform flow at the engine-face station.Starting characteristic was obtained through numerical simulation under various outflow back pressure.Calculations with bleed indicate that boundary layer bleed can be used to stabilize the terminal shock location and prevent choking of the inlet,which is beneficial to resist outflow back pressure.The presented method is applicable to preliminary inlet design and numerical simulation.