Calibration and application of a combination temperature-pneumatic probe for velocity and rotor loss distribution measurements in a compressor
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A description is given of the current design of a temperaturepneumatic probe used for radial flow field surveys in an axial compressor. The procedure used to calibrate the probe for variations in Mach number, pitch and yaw angles in a free jet is described and the procedure for representing the characteristics of the probe analytically as three polynomial surfaces, is given.
Interim Report. Principal Investigator, Dr. R. P. Shreeve, Director, Turbopropulsion Laboratory, Naval Postgraduate School, Monterey, California, 93940