Force Measurements on a NACA 0012 Wingtip at Mach 0.75

摘要

A NACA 0012 wingtip was tested at Mach 0.75 and chord Reynolds number of 3 million at incidences from -4 to 7 deg in a transonic Ludwieg tube. The Mach and Reynolds number are representative of fullscale blade conditions of rotorcraft blades. Due to the short test time of 0.1 s and high impulse loads, a dynamic calibration was applied to a conventional sidewall force balance. A unique set of lift and drag data were obtained.