This article presents correlations for indirect measurement of skin friction inside a laminar separation bubble induced by hypersonic shock-boundary layer interaction (SBLI) on a flat plate. The correlations, based on parameters that are known to influence the SBLI region, were developed using exhaustive numerical and analytical studies. Experiments were conducted in a hypersonic shock tunnel at Mach 8.6 (±0.22) to measure surface heat-flux and pressure in the zone of SBLI on a flat plate, which were then used to supplement and validate the correlations. The data predicted by the correlations agreed reasonably well with that of exact solutions. The case studies contained non-reacting air, behaving as a perfect gas on a flat surface.

本文介绍了用于间接测量由平板上的高超声速冲击边界层相互作用（SBLI）引起的层状分离气泡内皮肤摩擦的相关性。基于详尽的数值和分析研究，开发了基于已知影响SBLI区域的参数的相关性。在高超声速冲击隧道中以8.6马赫（±0.22）的速度进行了实验，以测量平板上SBLI区域中的表面热通量和压力，然后将其用于补充和验证相关性。由相关性预测的数据与精确解的数据相当吻合。案例研究包含未反应的空气，在平坦表面上表现为完美的气体。