Off-design correlation for losses due to part-span dampers on transonic rotors
William B. Roberts, James E. Crouse, Donald M. Sandercock, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Lewis Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1980 - Technology & Engineering - 21 pages
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100 percent 60 Radial location 80 Hub Radial 80 Hub Tip aerodynamic and geometric angle of attack area ruling aspect ratio 100 blade suction blade suction-surface incidence coefficient in region constant-area operating line damper angle damper location damper performance damper region data Estimated variation design point design speed drag coefficient equation Experimental data Estimated Hub Radial location Hub Tip 20 influenced by part-span large dampers Lewis Research Center loss and region loss due loss variation loss without damper Mach number maximum damper loss maximum flow maximum loss Midrange NASA rotor nozzle area operating point part-span damper percent of design percent of span Pratt & Whitney psd.m radial variation region influenced region of influence research rotors rotational speed rotor loss coefficient solid symbols denote span from tip speed line stall surface incidence tip at trailing trailing edge transonic rotors variation in damper variation of loss variation of rotor various operating conditions