Patents by Inventor Danny A. Sikavi

Danny A. Sikavi has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 12162588
    Abstract: High-performance winglets are provided for attachment to an airplane wing. A split blended winglet includes a blended or upper winglet smoothly extending from the wing tip above a chord plane of the wing and a lower winglet including a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet includes a blade section that projects vertically along a reverse curve before transitioning to a linear upper blade portion. Upper and lower surfaces of the upper winglet are bound by leading and trailing edges that are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Upper and lower surfaces of the lower winglet are bound by leading and trailing edges that curve toward the airstream direction and terminate at a point distal of the wing tip.
    Type: Grant
    Filed: January 7, 2020
    Date of Patent: December 10, 2024
    Assignee: Aviation Partners, Inc.
    Inventor: Danny A. Sikavi
  • Patent number: 11459093
    Abstract: A system and method for optimizing winglet airfoil geometries in the presence of interference conditions at cruise Mach speeds. The method includes performing a first analysis on the airfoil at a first Mach speed and a second Mach speed greater than the first Mach speed. The analyses provide resultant values that can include any one or more of a coefficient of lift (CL), a coefficient of drag (CD), and a coefficient of pressure (CP). A desired pressure distribution curve on the airfoil can be specified based on the resultant values. An inverse analysis can then be performed to derive a modified airfoil geometry that corresponds to the desired pressure distribution. The modified airfoil geometry can be incorporated into a blended winglet and analyzed by way of running a CFD++ code to verify improved airfoil performance in a full airplane geometry.
    Type: Grant
    Filed: February 22, 2019
    Date of Patent: October 4, 2022
    Assignee: Aviation Partners, Inc.
    Inventor: Danny A. Sikavi
  • Publication number: 20220097830
    Abstract: High-performance winglets are provided for attachment to an airplane wing. A split blended winglet includes a blended or upper winglet smoothly extending from the wing tip above a chord plane of the wing and a lower winglet including a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet includes a blade section that projects vertically along a reverse curve before transitioning to a linear upper blade portion. Upper and lower surfaces of the upper winglet are bound by leading and trailing edges that are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Upper and lower surfaces of the lower winglet are bound by leading and trailing edges that curve toward the airstream direction and terminate at a point distal of the wing tip.
    Type: Application
    Filed: January 7, 2020
    Publication date: March 31, 2022
    Inventor: Danny A. Sikavi
  • Publication number: 20190256197
    Abstract: A system and method for optimizing winglet airfoil geometries in the presence of interference conditions at cruise Mach speeds. The method includes performing a first analysis on the airfoil at a first Mach speed and a second Mach speed greater than the first Mach speed. The analyses provide resultant values that can include any one or more of a coefficient of lift (CL), a coefficient of drag (CD), and a coefficient of pressure (CP). A desired pressure distribution curve on the airfoil can be specified based on the resultant values. An inverse analysis can then be performed to derive a modified airfoil geometry that corresponds to the desired pressure distribution. The modified airfoil geometry can be incorporated into a blended winglet and analyzed by way of running a CFD++ code to verify improved airfoil performance in a full airplane geometry.
    Type: Application
    Filed: February 22, 2019
    Publication date: August 22, 2019
    Inventor: Danny A. Sikavi
  • Publication number: 20190256188
    Abstract: Systems and methods for reducing or weakening the shocks acting on an airfoil, such as an airfoil of an airplane wing. In one embodiment, the length of an airfoil is increased by shifting the trailing edge aft by installing a trailing edge extender. In one embodiment, the length and shape of an airfoil is changed by shifting the trailing edge aft and downward by installing a trailing edge extender. In one embodiment, an airfoil is changed by removing a portion of the wing at the trailing edge and increasing the camber by installing a trailing edge modifier to adjust the circulation surrounding the wing and redistribute loading of the wing. Modifications of an airplane wing, including installing a trailing edge extender, are easy to implement, do not require span extensions or tip devices, and improve fuel efficiency.
    Type: Application
    Filed: February 22, 2019
    Publication date: August 22, 2019
    Inventor: Danny A. Sikavi