Direct calibration framework of triple-hole pressure probes for incompressible flow

Abstract

This paper carries out a mathematical analysis of the limits and data reduction techniques of three-hole pressure (THP) probes operating in a ‘non-nulling’ mode for incompressible flow. As a result of this analysis, a direct procedure is advanced, based on the distinction of several zones within the angular range, where different relations can be applied to obtain the flow variables. This proposal provides a considerable increment of the operative angular range of THP probes: about ±70◦ instead of the typical ±35◦ for a cylindrical probe. This may extend the application of these probes in highly unsteady flows, or reduce the acquisition and data reduction effort minimizing the necessity of probe reorientation. The influence of the data reduction technique on the uncertainty transmission is also presented in the paper. From detailed considerations, it is demonstrated that the results uncertainty depends on the specific probe, but it is unaffected by the mathematical procedure employed to calculate the flow variables. Validation measurements with pneumatic probes have been made for Reynolds numbers from 4 × 103 to 3.5 × 104. In addition, a highly unsteady measurement in a low-speed axial flow fan is succinctly analysed. Taking into account both attainable angular range and uncertainty, it is determined that the optimal construction angle for the holes of a low frequency response THP probe lies between 30◦ and 60◦, while for fast response probes, in order to avoid the separated flow region, the optimal construction angle is around 30◦.