This paper presents in detail a method for measuring high subsonic two dimensional periodic flow field with a single hole cylindrical pressure probe with high frequency response.The method normalizes the probe calibration curves at different Mach number and simplifies the compressibility correction.The probe is set in nine azimuthal angles while measuring the flow.Sampled and averaged data are used to determine flow angles by least square fitting

Mach number and stagnation pressure are then obtained from solving a set of non linear equations.The method has been successfully applied to measuring the rotor exit flow field in a multistage compressor with high accuracy.