图  1  激波串在隔离段不同位置前移速度变化^[6]

Figure  1.  Velocities of a shock train moved forward in an isolator^[6]

图  2  隔离段内的速度分布^[7]

Figure  2.  Velocity contour of the flowfield in an isolator^[7]

图  3  激波串过程突跳纹影序列和壁面压力分布^[13]

Figure  3.  Schlierens and pressure distributions when a rapid movement of shock train occured^[13]

图  4  背景波系伸展过程中激波串突跳现象的数值纹影序列^[16]

Figure  4.  Sequence of schlierens when a rapid movement of shock train occurred^[16]

图  5  激波串下缘突跳前后的壁面压力分布^[15]

Figure  5.  Pressure distributions when a rapid movement of shock train occured^[15]

图  6  激波串前缘位置随当量比变化过程^[22]

Figure  6.  Climbing path of a shock train^[22]

图  7  激波串流场结构示意图^[24]

Figure  7.  Schematic of the flowfield with a shock train^[24]

图  8  等效喉道压缩结构示意图^[25]

Figure  8.  Sketch of the throat-like structure at shock train head^[25]

图  9  激波串前缘初始激波和附面层流场结构示意图^[25]

Figure  9.  Sketch of flowfield at shock train head^[25]

图  10  激波串前缘初始激波角与收缩极限的关系^[25]

Figure  10.  Relationship between angle of initial shock to contraction ratio^[25]

图  11  隔离段马赫数与收缩极限的关系^[25]

Figure  11.  Relationship between Mach number to the minimum value of contraction ratio^[25]

图  12  激波串突跳前后纹影图^[25]

Figure  12.  Schlierens of the flowfield when a rapid movement of shock train occurred^[25]

图  13  突跳前后等效喉道收缩比变化^[25]

Figure  13.  Contraction ratio of the throat-like structure when a rapid movement of shock train occurred^[25]

图  14  激波串前缘最小收缩极限分析示意图^[27]

Figure  14.  Sketch of the analysis method for the minimum value of the contraction ratio^[27]

图  15  角涡流线图^[28]

Figure  15.  Sketch of streamlines of corner vortex^[28]

图  16  角涡和中部分离涡的流场可视化^[29]

Figure  16.  Visualization of corner vortex and central vortex^[29]

图  17  激波入射引起的激波附面层交互与壁面摩擦系数分布^[30]

Figure  17.  Shock-boundary layer interactions and friction coefficient distribution induced by incident shock^[30]

图  18  三维效应下的流场速度分布^[31]

Figure  18.  Velocity contours of flowfield with sidewall effect^[31]

图  19  试验段构型和压力测点布置^[36]

Figure  19.  Configuration of test sections and the pressure measuring points^[36]

图  20  背压和挡板角度变化时序：(a)工况D，(b)工况E，(c)工况F。时间根据试验时长进行了无量化处理^[36]

Figure  20.  Time histories of the backpressure ratio and the flap angle: (a) case D, (b) case E, (c) case F. The time is non-dimensionalized by the total duration^[36]

图  21  试验过程中典型压力时序^[36]

Figure  21.  Comparisons of typical pressure histories during the test conditions^[36]

图  22  工况C和F中激波串前缘轨迹对比：(a)上壁面，(b)下壁面。时间根据试验时长进行了无量化处理^[36]

Figure  22.  Comparisons of the trajectories of the shock train leading edge with case C and case F conditions at the top wall (a) and bottom wall (b). The time is non-dimensionalized by the total duration^[36]

图  23  激波串运动物理过程简图^[37]

Figure  23.  Physical process of the shock train movement^[37]

图  24  无激波入射下低阶模型激波串前缘预估与试验结果比较^[37]

Figure  24.  Trajectories of the shock train leading edge estimated by the low-order model compared with the experimental values^[37]

图  25  模型预测激波串动态特性与数值模拟结果对比，背压压比变化为：(a) 2.83~3.05, (b) 3.05~3.39, (c) 3.39~3.62^[37]

Figure  25.  Dynamic features of the shock train compared with the CFD results, where backpressure ratio is from (a) 2.83 to 3.05, (b) 3.05 to 3.39, (c) 3.39 to 3.62^[37]

图  26  有激波入射下低阶模型激波串前缘预估与试验结果比较^[37]

Figure  26.  Trajectories of the shock train leading edge estimated by the low-order model compared with the experimental values under incident shocks^[37]