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Page count: 11

A limited calibration of a combined pitot-static tube and vane-type flow-angularity indicator has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01. The results indcate that the instrument registers too high an angle of attack and gives an error of 0.7 degrees at an angle of attack of 20 degrees for a Mach number of 1.61 and an errror of 1.6 degrees at an angle of attack of 24 degrees for a Mach number of 2.01. At zero angle of attack the flow field about the yaw vane was unsymmetrical and caused an error or 1.4 degrees in yaw indication at zero angle of yaw for a Mach number of 2.01. The installation of a dummy vane pedestal to provide a more symmetrical flow field reduced this error to 0.25 degrees. The probe gave static-pressure readings which were too low at angles of yaw.