NASA 5.2%-Scale Semispan High Lift Common Research Model High Reynolds Number Wind Tunnel Test in the National Transonic Facility

A wind tunnel test was conducted at the NASA Langley National Transonic Facility (NTF) from December 2023 through May 2024 on the NASA 5.2%-scale semispan High Lift Common Research Model (CRM-HL). Eight model configurations were tested including four landing, two landing with ice shapes installed, and two takeoff configurations. The test was run in both air and in nitrogen with tunnel freestream conditions ranging from -250degF and 150degF (-156degC to 49degC), a Mach number range of 0.20 to 0.35, and chord Reynolds numbers of 1.61 million to 30 million (matching flight Reynolds number). The force and moment and pressure data from this and other CRM-HL models will be made available to the worldwide research community to allow for comparison between different wind tunnels and different configurations to improve the state-of-the-art in CFD, and to increase wind tunnel testing knowledge. This paper will give an overview of the NASA 5.2%-scale CRM-HL high Reynolds number test that was run at NTF. Some data will be presented to show repeatability and to present some basic model testing information.