Abstract: Hot-wire probes have been calibrated in FL-23 transonic and supersonic wind tunnel of CARDC (China Aerodynamics Research and Development Center). The calibration results have shown that at aw>0.6, the sensor sensitivity coefficient S. almost does not change with aw; at. aw= 0.8 and Ma=0.60~ 1.16, Sp almost does not vary with Mach number. The mean flow and fluctuating flow characteristics within boundary layer of FL-23 wind tunnel's test section side wall have been measured by the calibrated hot-wire. The boundary layer mean flow characteristics measured by the hot wire are in good agreement with those measured by Pitot tube. Fluctuating velocity and density. (u' /u- and p'/p) measured by the hot-wire within boundary layer have shown that neither u' /u nor p' /p decreases monotonously with the increase of distance y from the tunnel wall.

Key words: transonic flow, boundary layer, turbulent measurement, hot-wire anemometers