THIS PROJECT AIMS TO EXPAND THE DATASET PROVIDED TO NASA BY PURDUE UNIVERSITY UNDER THE SUCCESSFUL COMPLETION OF AWARD NNX11AI59A FOR THE SUBSONIC FIXED WING PROJECT TOPIC A.2.5: UNDERSTANDING AND MITIGATING TIP LEAKAGE AND END WALL LOSSES IN HIGH PRESSURE RATIO CORES. IN THAT PROJECT DETAILED MEASUREMENTS WERE ACQUIRED ON THE PURDUE THREE-STAGE AXIAL RESEARCH COMPRESSOR FOR 3 ROTOR TIP CLEARANCES: 1.5% 3% AND 4% (BASED ON SPAN). SOME OF THE KEY COMPONENTS OF THE DATASET INCLUDES: PERFORMANCE MAPS DETAILED TRAVERSE DATA AT THE EXIT OF EVERY BLADE ROW FOR A COUPLE OF LOADING CONDITIONS AT 100% CORRECTED SPEED FOR THE 1.5%&4% CLEARANCES AND ROTOR TIP LEAKAGE FLOW TRAJECTORY MEASUREMENTS FROM OVER-ROTOR STATIC PRESSURES. AS NASA RESEARCHERS HAVE USED THE DATA TO RUN CFD SIMULATIONS IT HAS BECOME CLEAR THAT BETTER DEFINITION OF THE LEAKAGE UNDER THE KNIFE SEALS OF STATOR 1 AND STATOR 2 ARE REQUIRED TO GET THE RIGHT STAGE MATCHING IN THE SIMULATIONS. THUS DATA WILL BE ACQUIRED TO QUANTIFY THE LEAKAGE FLOW THROUGH THE KNIFE SEALS. ALSO ADDITIONAL DETAILED MEASUREMENTS OF THE TOTAL PRESSURE FIELD WILL BE ACQUIRED AT 3% CLEARANCE SO THAT PARAMETERS SUCH AS TIP LEAKAGE VORTEX SIZE AND PENETRATION CAN BE STUDIED AND COMPARED TO PREVIOUSLY ACQUIRED RESULTS FOR THE 1.5% AND 4% CLEARANCE CONFIGURATIONS. FINALLY UNEXPECTED TRENDS IN THE ROTOR TIP LEAKAGE FLOW TRAJECTORY WERE REPORTED IN AWARD NNX11AI59A. TO TEST HYPOTHESES AS TO WHY THESE TRENDS WERE FOUND THE OVER-ROTOR CASING STATIC PRESSURE MEASUREMENTS WILL BE ACQUIRED ON EACH CLEARANCE CONFIGURATION (1.5% 3% AND 4%) FOR OPERATING CONDITIONS THAT MATCH THE RATIO OF PRESSURE RATIO TO CORRECTED MASS FLOW RATE OR STALL MARGIN TO SEE IF THESE CONDITIONS GOVERN THE LEAKAGE FLOW TRAJECTORY.