Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave.

超音速飞行器中配备的光学设备由于航空光学效应而受到光路畸变的影响，有可能导致传感和成像性能下降。在这项研究中，通过实验和数值方法研究了超声速流在二维压缩坡道上的航空光学效应。通过使用二维Shack-Hartmann传感器测量通过超音速风洞的测试段传播的激光束的波前来进行实验。冲击波和边界层对波前畸变的单独贡献是通过对由求解雷诺平均Navier-Stokes方程的二维数值模拟获得的流场密度进行射线追踪计算来确定的。将数字获得的波前与使用Shack-Hartmann传感器测得的时间平均波前进行比较。分析了光线在激光束中心的偏转角，以评估由冲击波和边界层引起的航空光学效应。针对激光束的各种入射角，分析了冲击波和边界层对波前畸变的单独影响。对于本实验装置，由于顶壁和底壁处的边界层具有与密度梯度相反的方向，因此产生的激光束偏转主要由整个冲击波上的密度梯度控制。分析了光线在激光束中心的偏转角，以评估由冲击波和边界层引起的航空光学效应。针对激光束的各种入射角，分析了冲击波和边界层对波前畸变的单独影响。对于本实验装置，由于顶壁和底壁处的边界层具有与密度梯度相反的方向，因此产生的激光束偏转主要由整个冲击波上的密度梯度控制。分析了光线在激光束中心的偏转角，以评估由冲击波和边界层引起的航空光学效应。针对激光束的各种入射角，分析了冲击波和边界层对波前畸变的单独影响。对于本实验装置，由于顶壁和底壁处的边界层具有与密度梯度相反的方向，因此产生的激光束偏转主要由整个冲击波上的密度梯度控制。