为了减弱亚燃冲压发动机进气道扩张段中激波/边界层干扰引起的边界层分离现象,文中提出了一种基于边界层剥离的主动控制方法,即通过可动隔板将边界层低速流排出进气道。数值研究发现,该方法可使扩张段内边界层分离明显减弱、结尾激波链长度变短直至消失,从而实现进气道抗反压能力显著提高、最大总压恢复系数显著增加、出口流场品质明显改善。

For weakening the shock-wave/boundary layer interaction separation in the subsonic diffusion sector of ramjet inlet, a control method based on boundary layer stripping was presented. The boundary layer low speed flow was discharged from the inlet with adjustable partitions. The numerical investigation indicates that with the method, the shock-wave/boundary layer interaction separation is dramatically weakened and the end shock-wave chain becomes shorter even vanishes, which result in a marked increase of the anti-back pressure capability, a significant increase of the maximum total pressure recovery coefficient, and the exit flow field quality is obviously improved.