High-Lift Device Testing in JAXA 6.5M X 5.5M Low-Speed Wind Tunnel

Abstract

To obtain detailed validation data for a complicated high-lift system including aerodynamics, aeroacoustics, flow visualization, and so on, half-span large-scale high lift device model was tested in JAXA 6.5m x 5.5m Low-speed Wind Tunnel. Five-component aerodynamic force and aeroacoustic noise with phased array microphones were measured simultaneously, and surface pressure with pressure taps and Pressure Sensitive Paint (PSP), unsteady pressure using surface mounted pressure sensors, and velocity distribution around the model using Particle Image Velocimetry (PIV) were obtained. Surface flow visualization with oil flow and china clay method were also carried out. Here, overview of the testing and verification data for CFD which were successfully obtained is reported. Moreover, those various measurements were able to reveal important aspects of flow field around nacellepylon which dramatically affected to aerodynamic force, surface pressure, and also aeroacoustic noise.