A method and system delay the laminar-to-turbulent transition of a supersonic or hypersonic boundary layer flow moving in a flow direction over a surface. For supersonic boundary layer flow, oblique first-mode instability waves present in the boundary layer and propagating at an oblique angle relative to the flow direction cause a laminar-to-turbulent transition in the boundary layer flow. These instability waves have a wavelength associated therewith in a direction perpendicular to the flow direction. Flow disruptors are used to generate modulations within the boundary layer flow wherein a wavelength of the modulations along the direction perpendicular to the flow direction is less than one-half of the wavelength of the instability waves. For hypersonic boundary layer flow, the flow disruptors generate modulations within the boundary layer flow wherein the wavelength of the modulations is less than streak spacing for optimal transient growth or, equivalently, in the range of one to two times the boundary layer thickness.


    Access

    Download


    Export, share and cite



    Title :

    Method and system for delaying laminar-to-turbulent transition in high-speed boundary layer flow


    Contributors:

    Publication date :

    2020-08-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow

    PAREDES GONZALEZ PEDRO / CHOUDHARI MEELAN M / LI FEI | European Patent Office | 2018

    Free access



    Laminar-Turbulent Transition in a Swept Low-Speed Boundary Layer

    Bahrainirad, Ladan / Hosseinverdi, Shirzad / Fasel, Hermann F. | AIAA | 2022


    In-flight experiments for delaying laminar—turbulent transition on a laminar wing glove

    Peltzer, I / Pätzold, A / Nitsche, W | SAGE Publications | 2009