초록 ▼

An airfoil family for a helicopter rotor blade, designated SC362XX. SC362XX essentially removes the large lower surface suction peak associated with ‘drag creep’ at moderate lift coefficients while reducing the peak Mach number and shock strength at high lift/Mach number conditions. Another optional

An airfoil family for a helicopter rotor blade, designated SC362XX. SC362XX essentially removes the large lower surface suction peak associated with ‘drag creep’ at moderate lift coefficients while reducing the peak Mach number and shock strength at high lift/Mach number conditions. Another optional airfoil family for use at inboard regions of the helicopter rotor, which is designated SC3252XX airfoil family, is a relatively thicker airfoil section that includes a significant increase in thickness forward of the 30% x/c location to provide a relatively thick and rigid inboard section. The lift coefficient at which the drag divergence Mach number was optimized is the same in both families thereby readily providing application to a single rotor blade.

대표청구항 ▼

1. A main rotor blade of a single rotor helicopter comprising: a tip region of a main rotor blade, said tip region including an airfoil profile section which defines an airfoil thickness along a chord line within said airfoil profile section, said airfoil profile section having leading edge and a tr

1. A main rotor blade of a single rotor helicopter comprising: a tip region of a main rotor blade, said tip region including an airfoil profile section which defines an airfoil thickness along a chord line within said airfoil profile section, said airfoil profile section having leading edge and a trailing edge, an upper airfoil surface and a lower airfoil surface which extend between said leading edge and said trailing edge as defined by a set of coordinates in which an airfoil thickness is plotted against a non-dimensional distance from said leading edge of said airfoil profile section along said chord line, as a set of Y/C coordinates scaled by a desired factor at a given X/C as listed in Table I, wherein X is the linear displacement along the chord line extending between the leading edge and the trailing edge,C is the chordal length of the airfoil cross section measured between the airfoil leading edge and the airfoil trailing edge; andY is a transverse displacement of the airfoil surface from the chord line. 2. The main rotor blade as recited in claim 1, wherein said tip region is defined by an outboard 15% of the main rotor blade. 3. The section as recited in claim 1, wherein said airfoil profile section is defined by a scaled set of coordinates in which said set of Y/C coordinates listed in Table I are scaled by a factor of 1.2 while said X/C values are unchanged. 4. The section as recited in claim 1, wherein said X/C values in Table I are unchanged. 5. The section as recited in claim 1, wherein said airfoil profile section extends into a main section of said main rotor blade.