Direct numerical simulations of a spatially developing Ma 2.25 supersonic turbulent boundary layer with streamwise-striped wall blowing (SSB) are performed for the purpose of turbulence drag reduction. The SSB is designed to blow through long and straight slots in the flow direction. The slots are equally distributed in spanwise direction, with different stripe spacing and width. Blowing amplitudes of 0.1% and 0.2% are investigated. For comparison, uniform blowing (UB) of 0.1% is also simulated. It is found that in spite of weak control amplitudes, 7.4% and 14.5% drag reduction can be achieved in the case of 6SSB 0.1% and 6SSB 0.2%, respectively. Similar to UB, the boundary layer displacement thickness is thickened by SSB, with a thicker viscous sub-layer and a logarithmic zone which moving away from the wall. Turbulence intensities and turbulent coherent structures are enhanced, although the streamwise scales of the latter are attenuated. Turbulent kinetic energy analysis presents that both the production and dissipation are increased in the near wall. Compressible Renard-Deck decomposition of $C_f$ shows that it is the spatially growth term that mainly responsible for the turbulence drag reduction.

在空间上发展的Ma的直接数值模拟为了减少湍流阻力，进行了2.25超音速湍流边界层和流式条纹吹壁（SSB）。SSB旨在沿流动方向吹过长而直的槽。缝隙在翼展方向上均匀分布，具有不同的条带间距和宽度。研究了0.1％和0.2％的吹塑振幅。为了进行比较，还模拟了0.1％的均匀吹气（UB）。已发现，尽管控制幅度较弱，但在6SSB为0.1％和6SSB为0.2％的情况下，阻力可分别降低7.4％和14.5％。类似于UB，边界层位移厚度通过SSB进行了加厚，具有较厚的粘性子层和对数区，并且远离壁移动。湍流强度和湍流相干结构得到增强，尽管后者的水流尺度被减弱了。湍流动能分析表明，近壁处的产生和耗散均增加。可压缩的Renard-Deck分解$C_F$ 结果表明，空间增长项是造成湍流阻力减小的主要原因。