High-speed PIV applied to wake of NASA CRM model at high Re-number sub- and transonic stall conditions

Abstract

Within the framework of the EU project ESWIRP, the particle image velocimetry (PIV) using high-speed camera and laser has been used to measure the turbulent flow in the wake of a stalled aircraft wing. The measurements took place on the common research model provided by NASA in the pressurized cryogenic European Transonic Wind tunnel. A specific cryoPIV system has been used and adapted for using high-speed PIV components under the cryogenic conditions of the wind tunnel facility. First results are presented comprising transonic and subsonic stall conditions at realistic flight Reynolds numbers of 11.6 and 30 million, respectively.