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
What people are saying - Write a review
We haven't found any reviews in the usual places.
100 percent 80 Hub Radial aerodynamic and geometric angle of attack area ruling aspect ratio 100 Axial-Flow blade suction blade suction-surface incidence coefficient in region constant-area operating line Cunnan damper angle damper location damper performance damper region data Estimated variation design point design speed Donald equation Experimental data Estimated Hub Radial location 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 NASA TM nozzle area operating point part-span damper percent of design percent of span Pratt & Whitney psd.m radial variation reading region influenced region of influence research rotors rotational speed rotor loss coefficient shock loss span from tip speed line stall surface incidence tip at trailing trailing edge Transonic Fan Stage transonic rotors Urasek variation in damper variation of loss variation of rotor various operating conditions wpsd