Comparison of three methods for calculation of helicopter rotor blade loading and stresses due to stall
National Aeronautics and Space Administration, 1974 - Aerodynamic load - 21 pages
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0arget 77 stall 7oeing stall aerodynamic lift force Air Mobility R&D American Helicopter Society Ames Research Center angle of attack angle-of-attack distribution Army Air Mobility bending moments differ Boeing stall method CALCULATION OF HELICOPTER coefficient considered predict essentially cyclic pitch data for eg dc/V differ by 25 drag coefficient DUE TO STALL dynamic-stall methods considered effects of dynamic eg and cm elastic torsion Figure HELICOPTER ROTOR BLADE inflow distribution mean bending moments methods considered predict METHODS FOR CALCULATION Mobility R&D Laboratory Moffett Field motion and stresses NACA no-stall nonuniform inflow operating condition parasite drag particularly the aerodynamic peak-to-peak torsion performance and trim Polar plot propulsive force rotor at high ROTOR BLADE LOADING Section aerodynamic lift Section aerodynamic pitching side force stall effects static airfoil data static stall three dynamic stall three dynamic-stall methods three methods tip path plane torsion and bending TRIM DATA U.S. Army U70 stall UARL Method