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.
USM3D Analyses of Transonic Boundary Layer Thickener Configurations Applied to Fuselage
Journal of Aircraft ; 58 , 4 ; 781-792
2021-03-26
12 pages
Article (Journal)
Electronic Resource
English