IGF::OT::IGF HIGH EFFICIENCY HIGH OPR CAPABLE SMALL CORE COMPRESSOR. A PRIMARY GOAL OF THE FIXED WING PROJECT IS TO REDUCE FUEL BURN BY 60% FOR N+3 SINGLE-AISLE TRANSPORT AIRCRAFT (E.G. BOEING-737 CLASS AIRBUS-320 CLASS). WORKING TOWARD THIS GOAL THE OBJECTIVE IS TO DEVELOP AND DEMONSTRATE TECHNOLOGIES TO MITIGATE AERODYNAMIC LOSSES DUE TO LARGE BLADE TIP CLEARANCE/ENDWALL EFFECTS AND TO IMPROVE THE PERFORMANCE OF SMALL HIGH PRESSURE TURBOMACHINERY (COMPRESSOR OR TURBINE) CORE STAGES TO ENABLE FUEL BURN BENEFITS FOR N+3-RELEVANT ENGINES. THE ENGINES OF INTEREST ARE CHARACTERIZED BY HIGHER OVERALL PRESSURE RATIO (OPR>50) CYCLES AROUND 20 000 TO 30 000 POUNDS THRUST WITH BYPASS RATIOS FROM 12-18 AND ASSOCIATED SMALLER CORES 1500F DISK RIM AND SEAL MATERIAL CAPABILITY AND UNCOOLED CERAMIC TURBINE BLADES. COMPRESSOR EXIT CORRECTED MASS FLOW RATES SIGNIFICANTLY LOWER THAN CURRENT PRACTICE ARE REQUIRED TO ACHIEVE THE HIGH OVERALL PRESSURE RATIO FOR THIS THRUST CLASS.