Aerodynamic Performance of 0.5-meter-diameter, 337-meter-per-second Tip Speed, 1.5-pressure-ratio, Single-stage Fan Designed for Low Noise Aircraft Engines
National Aeronautics and Space Administration, 1974 - Aerodynamic load - 181 pages
Overall and blade-element aerodynamic performance of a 0.271-scale model of QF-1 are presented, examined, and then compared and evaluated with that from similar low noise fan stage designs. The tests cover a wide range of speeds and weight flows along with variations in stator setting angle and stator axial spacing from the rotor. At design speed with stator at design setting angle and a fixed distance between stage measuring stations, there were no significant effects of increasing the axial spacing between rotor stator from 1.0 to 3.5 rotor chords on stage overall pressure ratio, efficiency or stall margin.
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100 PERCENT DESIGN ABS BETAM REL ABS MACH ABS VEL REL BETAM REL BETAM BETAM TOTAL TEMP blade COEFF LOSS PARAM D-FACT EFF LOSS design setting angle DEV D-FACT EFF EFF LOSS COEFF exit pylons INCIDENCE DEV D-FACT INSTRUMENTATION AT STATION INTRABLADE ROW INSTRUMENTATION LOSS COEFF LOSS LOSS PARAM RP MACH NC MACH NO MERID MACH NO REL MEAN SS TOT measuring station 2a MERID MACH MERID PEA MERID PEAK SS MERID VEL TANG PARAM RP SPAN PERCENT DESIGN SPEED PERCENT INCIDENCE DEV percent of design PROF TOT PROF RADII ABS BETAM RATIO IN RATIO Reading number REL BETAM TOTAL REL MACH REL VEL MERID reset stator ROTOR 15 RP SPAN MEAN span from tip SPAN MEAN SS SS TOT PROF STATOR 9 90 STATOR RESET TANG VEL WHEEL TEMP TOTAL PRESS TOT PROF TOT TOTAL PRESS RP TOTAL PRESSURE RATIO TOTAL TEMP TOTAL WHEEL SPEED RP WT FLOW