초록 ▼

This invention relates to airfoils which have particular application to rotors of helicopters and rotorcraft and to aircraft propellers. Two airfoil profiles, the RC(4)XX and RC(5)XX are shaped to permit (1) the development of high air loads without causing an extensive separation of the boundary la

This invention relates to airfoils which have particular application to rotors of helicopters and rotorcraft and to aircraft propellers. Two airfoil profiles, the RC(4)XX and RC(5)XX are shaped to permit (1) the development of high air loads without causing an extensive separation of the boundary layer air, (2) a distribution of airloads which results in a near zero pitching moment coefficient about the quarter chord for a range of lift coefficients from -0.2 to 1.0 for Mach numbers up to 0.63, and (3) the development of a local supersonic flow field which is so shaped that the wave losses are minimal until higher free stream Mach numbers over a range of lift coefficients from 0.0 to 0.30. Thus, both airfoils have high maximum lift coefficients, low pitching moment coefficients, and high drag divergence Mach numbers to result in improved rotor or propeller performance. The two invention airfoils are related in shape and purpose. The use of either airfoil by itself or the use of one in conjunction with the second would depend upon the design requirements of the particular application.

대표청구항 ▼

An airfoil for a rotating blade such as a helicopter blade or airplane propeller which provides for operation at higher lift coefficients than previous airfoils before stalling at Mach numbers from near zero to about 0.50 and which simultaneously provides both near zero pitching moments about the qu

An airfoil for a rotating blade such as a helicopter blade or airplane propeller which provides for operation at higher lift coefficients than previous airfoils before stalling at Mach numbers from near zero to about 0.50 and which simultaneously provides both near zero pitching moments about the quarter chord and low drag coefficients for a broad range of lift coefficients and Mach numbers, comprising: an airfoil means having an upper surface means, a lower surface means, an upper surface leading edge area, a lower surface leading edge area, and a trailing edge; said upper surface means having a surface slope which is positive and decreasing from the position where it fairs into said upper surface leading edge area to a position at approximately 37% chord, a surface slope which is negative and decreasing from approximately 37% chord to approximately 70% chord, and a surface slope which is negative and increasing from approximately 70% chord to said trailing edge: said lower surface means having a surface slope which is negative and increasing from the position where it fairs into said lower surface leading edge area to a position at approximately 9% chord, a surface slope which is positive and increasing from approximately 9% chord to approximately 19% chord, a surface slope which is negative and decreasing from approximately 19% chord to approximately 42% chord, and a surface slope which is positive and increasing from approximately 42% chord to said trailing edge.