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US 6,578,798 B1Granted
Airlifting surface division
OwnerFaruk Dizdarevic, Mithad Dizdarevicinventors
Life of this patent
Estimating the term…
Abstract
This airlifting surface division idea provides for division of airlifting surfaces resulting in low induced and interference drag. It can be applied to aircraft wings and helicopter and windmill rotor blades to significantly reduce induced drag when compared to prior art. Also, it can be used for new concepts of large subsonic and hypersonic aircraft to significantly reduce their overall drag and external dimensions when compared to prior art, simultaneously providing for very good pitch maneuver and longitudinal stability of such aircraft.
Claims4
An airlifting surface assembly being shaped for subsonic speed having a longitudinal and a transverse axis, said longitudinal axis coinciding with the direction of airflow, said airlifting surface assembly comprising:
- a main section, a transforming section, a leading section, and a following section, said main section extending along said transverse axis and having an upper and an under surface, a leading and a trailing edge, the main section upper and under surfaces having smooth and continuous curvatures, said transforming section being joined the outboard end of said main section and extending along said transverse axis, said transforming section having an upper and an under surface, a leading and a trailing edge, the transforming section upper surface having a smooth and continuous curvature and being tangentially joined said main section upper surface, the transforming section leading and trailing edges being tangentially joined the main section leading and trailing edges respectively, the transforming section under surface being tangentially joined said main section under surface, said transforming section under surface gradually bulging up towards said transforming section upper surface from the transforming section inboard end to the transforming section outboard end, thereby forming one concave and two convex curvatures in the direction of airflow, the vertex of said concave curvature approaching said transforming section upper surface and joining it on said transforming section outboard end in a point of division, thus dividing said transforming section into said leading and said following section, said leading section extending along said transverse axis and having an upper and an under surface, a leading and a trailing edge, and a trailing edge strake, the leading section upper and under surfaces having smooth and continuous curvatures and being tangentially joined said transforming section upper and under surfaces respectively, the leading section leading edge being tangentially joined said transforming section leading edge, said following section extending along said transverse axis and having an upper and an under surface, a leading and a trailing edge, and a leading edge strake, the following section upper and under surfaces having smooth and continuous curvatures and being tangentially joined said transforming section upper and under surfaces respectively, the following section trailing edge being tangentially joined said transforming section trailing edge, the leading section trailing edge strake is joined the following section leading edge strake in said point of division, said main and transforming sections being a main portion of said airlifting surface assembly, said leading section being a fore winglet, and said following section being an aft winglet of said airlifting surface assembly, said fore and aft winglets are differentially arching upward in the direction that is perpendicular to said longitudinal and transverse axes with said aft winglet trailing said fore winglet, whereby significantly reducing induced and interference drag of said airlifting surface assembly.
An airlifting body being shaped for subsonic and transonic speed having a plane of symmetry and a transverse axis that is perpendicular to said plane of symmetry, said plane of symmetry being defined by a longitudinal and a vertical axis, said longitudinal axis coincides with the direction of airflow, said airlifting body comprising:
- a main section, two mutually symmetrical transforming sections, two mutually symmetrical leading sections, and two mutually symmetrical following sections, said main section extending along said transverse axis on both sides of said plane of symmetry, said main section having an upper and an under surface, a leading and a trailing edge, the main section upper and under surfaces having smooth and continuous curvatures, said transforming sections join the outboard ends of said main section, each of said transforming sections extending along said transverse axis and having an upper and an under surface, a leading and a trailing edge, the transforming section upper and under surfaces sharing a point of division, said point of division being disposed on the transforming section outboard end, said transforming section upper surface having a smooth and continuous curvature and being tangentially joined said main section upper surface, said transforming section under surface being tangentially joined said main section under surface, said transforming section under surface gradually bulging tip towards said transforming section upper surface from the transforming section inboard end to said transforming section outboard end, thereby forming one concave and two convex curvatures in the direction of airflow, the vertex of said concave curvature approaching said transforming section upper surface and shifting toward said point of division in the direction of said longitudinal axis, said vertex is joined said transforming section upper surface in said point of division, thus dividing said transforming section into said leading and said following section, said leading and following sections extending along said transverse axis, each of said leading sections having an upper and an under surface, a leading and a trailing edge, and a trailing edge strake, said leading section upper and under surfaces having smooth and continuous curvatures and being tangentially joined said transforming section upper and under surfaces respectively, the leading section leading edge being tangentially joined said transforming section leading edge, each of said following sections having an upper and an under surface, a leading and a trailing edge, and a leading edge strake, the following section upper and under surfaces having smooth and continuous curvatures and being tangentially joined said transforming section upper and under surfaces respectively, said leading edge strake being joined said trailing edge strake in said point of division, said main section with said transforming sections being a main airlifting surface of an airplane, said leading sections being external fore airlifting surfaces of said airplane, and said following sections being external aft airlifting surfaces of said airplane, whereby significantly reducing overall drag and simultaneously providing for a sufficient pitch maneuver and longitudinal stability of said airplane.
An airlifting body being shaped for hypersonic speed having a plane of symmetry and a transverse axis that is perpendicular to said plane of symmetry, said plane of symmetry is defined by a longitudinal and a vertical axis, said longitudinal axis coinciding with the direction of airflow, said airlifting body comprising:
- a main section, two mutually symmetric transforming sections, two mutually symmetric leading sections and two mutually symmetric following sections, said main section extending along said transverse axis on both sides of said plane of symmetry, said main section having an upper and an under surface, a leading and a trailing edge, the main section upper and under surfaces having smooth and continuous curvatures, said transforming sections join the outboard ends of said main section, each of said transforming sections extending along said transverse axis and having an upper and an under surface, a leading and a trailing edge, the transforming section upper and under surfaces sharing a point of division, said point of division being disposed on the transforming section outboard end, said transforming section upper surface having a smooth and continuous curvature and being tangentially joined said main section upper surface, the transforming section leading edge being tangentially joined the main section leading edge, said transforming section under surface being joined said main section under surface in one continuous line in the direction of airflow, said transforming section under surface gradually bending upward from the transforming section inboard end to said transforming section outboard end, thus forming a concave bend in the direction of airflow, the vertex of said concave bend approaching said transforming section upper surface and shifting toward said point of division in the direction of airflow, said vertex being joined said transforming section upper surface in said point of division, thus dividing said transforming section into said leading and said following section, said leading and following sections extending along said transverse axis, each of said leading sections having an upper and an under surface, a leading and a trailing edge, the leading section upper surface having a smooth and continuous curvature and being tangentially joined said transforming section upper surface, the leading section under surface is joined said transforming section under surface in one continuous line in the direction of airflow, the leading section leading edge being tangentially joined said transforming section leading edge, each of said following sections having an upper and an under surface, a leading and a trailing edge, the following section upper surface having a smooth and continuous curvature and being tangentially joined said transforming section upper surface, the following section under surface is joined said transforming section under surface in one continuous line in the direction of airflow said main section with said transforming sections being a main airlifting surface of a hypersonic airplane, said teading sections being external fore airlifting surfaces of said airplane, and said following sections being external aft airlifting surfaces of said airplane, whereby significantly increasing lift versus drag ratio and simultaneously providing for a sufficient longitudinal stability and pitch maneuver of said airplane.
Dependencies are inferred from the claim text.