A rapid technique for measuring and visualizing the extent of separated flow

A method is described for rapidly measuring and visualizing the extent of separated flow suitable for a wind tunnel environment. The method utilizes a continuously swinging total pressure probe. This technique permits acquiring and presenting graphical records of separated regions in a fraction of the time required by other methods. Typical results indicate the presence of highly complicated three-dimensional separated regions for a typical general aviation twin-engine aircraft at post-stall conditions.List of Symbols c wing mean geometric chord - c_pt total pressure coefficient, (P _T-P_S)/q - P _S static pressure - P _T total pressure - q free stream dynamic pressure - q local dynamic pressure - r radial direction - x streamwise coordinate (x=0 corresponds to leading edge of wing) - angle of attach - azimuth direction