Effects of planform geometry on hover performance of a 2-meter-diameter model of a four-bladed rotor
Arthur E. Phelps, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, United States. Army Aviation Systems Command, United States. Army Aviation Research and Technology Activity. Aerostructures Directorate, Langley Research Center
National Aeronautics and Space Administration, 1986 - Technology & Engineering - 30 pages
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2MRTS 3-to-1 taper ratio aerodynamic characteristics aeroelastic airfoil section angle of attack baseline blade Baseline planform better hover performance blade planform blade span TR3 Cartesian coordinates Comparison of aerodynamic equation experimental data figure of merit flow separation FM curve ft/sec fully articulated hub fuselage general-research Helicopter Hover tests Langley Research Center low Reynolds number measured performance model blade Momentum Simplified free momentum strip-theory analysis NASA outboard 20 percent Prescribed wake Momentum prescribed-wake analysis prescribed-wake and momentum range of thrust range of tip reference 9 rotor blades Rotor Hover Performance shown in figure Simplified free wake simplified free-wake analysis Source o Experiment span TR5 tapered blades tapered configurations Tests were conducted three rotors tip Reynolds number tip speed tip vortex torque-required curves TR3 and TR5 TR3 planform TR5 blade TR5 configurations U.S. Army Vtip wake geometry wake Momentum High wake Momentum Low wake Momentum Simplified worse than measured Ст