The Development of a 3D Fast Response Aerodynamic Probe

Abstract

rcribes the application of surface mounted semiconductor pressure sensors to two and three dinmnsional fast response aerodynamic probe geometries. A detailed experimental programme or work is described in which large scale aerodynamic models of potential probe geometries have been tested at representative Reynolds numbers and a range of pitch and yaw configurations. The construction of small scale fast response aerdynamic probes is detailed , and calibration results obtained with these at a variety of Mach and Reynolds number conditions are given. INTRODUCTiON Pneumatic aerodynamic probes have been used for several decades in turbomachinery related research in order to determine fluid flow total and static pressures. Combination type probes have enabled flow Mach number and direction to bedetermined in two dimensions using mcasurements taken from three ports. Careful calibration of the probe, in terms of sensitivity to Mach and Reynolds number, is carried out in some form of aerodynamic calibration facility, where the effects of flow pitch and yaw on the measured acroydnamic coefficients aredctcrmincd. The probe is then introduced into the experiment where. measurements of llow quantities are required.