Calibration of pneumatic multi-hole probes for transonic turbomachinery flows

Abstract The calibration data of a five-hole probe and six-hole designed for measurements in transonic turbomachinery flows are presented. probes feature special base pressure hole on the back side to avoid Mach number insensitivity near unity. There is only little literature available performance such probes, especially with large radial flow angles. To close this gap, calibrated angles up 32 $$^\circ$$ ∘ . A significant influence angle coefficients used determination shown. At positive angles, relationship between coefficient using not biunique probe. Therefore, an experimental study measurement deviations performed at wind tunnel. Different evaluation methods examined. sample standard deviation over 210 randomly distributed points reduced by 66% compared same design without hole. This achieved two simultaneously multidimensional interpolation.