03.2 - Experimental Aerodynamics
AERODYNAMIC CHARACTERISTICS OF 8% SCALE SEMI-SPAN HIGH-LIFT COMMON RESEARCH MODEL AT THE JAXA 6.5M X 5.5M LOW SPEED WIND TUNNEL
M. Kohzai¹, M. Murayama¹, A. Sansica¹, D. Lusher¹, T. Takaishi¹, H. Abe¹; ¹Japan Aerospace Exploration Agency, Japan
JAXA participates in the international framework “CRM-HL Ecosystem” for the purpose of verifying CFD technology development of high-lift configurations and has prepared an 8% half-span high-lift configuration of the NASA Common Research Model (CRM-HL). This presentation will introduce an overview of the wind tunnel model and test plan. Early 2025, wind tunnel tests were conducted in JAXA's 6.5m x 5.5m low-speed wind tunnel to obtain the basic performance of the CRM-HL model and to investigate the noise reduction effect of the high-lift device and main landing gear. Aerodynamic coefficients, pressure distribution, unsteady pressure, and noise source measurements were conducted and here shown. Flow visualization over the tufted wing was also conducted on the baseline configuration. Furthermore, tests to understand aerodynamic phenomena in the stall region were conducted in November 2025, including aerodynamic coefficients, pressure distribution, surface visualization using oil flow, and PIV measurements. The results of these tests on the baseline configuration are reported.
DOI: 10.71945/icas2026_0256