A wind tunnel test was performed in the 0.3-Meter Cryogenic Transonic Tunnel at the NASA Langley Research Center to investigate the impact of various boundary layer thickeners on the height and shape of the boundary layer on the aft portion of a half-fuselage model. The present paper discusses USM3D analyses that were performed in support of the wind tunnel test. The results consisted of comparisons between USM3D and experimental data for the baseline configuration and two boundary layer thickening configurations. The comparisons considered surface pressure distributions, boundary layer profiles, and calculated boundary layer thicknesses. Additionally, a grid refinement study was performed for each of the three configurations, which illustrated general improvement in the comparisons with increasing grid refinement. Overall, the comparisons show favorable agreement between the USM3D predictions and the experimental data.

在美国宇航局兰利研究中心的0.3米深冷跨音速隧道中进行了风洞试验，以研究各种边界层增稠剂对半机身模型后部边界层的高度和形状的影响。本文讨论了为支持风洞测试而进行的USM3D分析。结果包括USM3D与基线配置和两个边界层增厚配置的实验数据之间的比较。比较考虑了表面压力分布，边界层轮廓和计算出的边界层厚度。此外，针对这三种配置中的每一种进行了网格细化研究，结果表明，随着网格细化程度的提高，比较中的总体改进。全面的，