Computational model for the calculation of the flow about wings with leading-edge vortices

H. W.M. Hoeijmakers*, B. Bennekers

*Corresponding author for this work

    Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

    Abstract

    A Computational method is presented for the calculation of the incompressible flow about wings with leading-edge vortices. The mathematical model replaces the spiralling free shear layer springing from the leading edge by a free vortex sheet which is terminated by a combination of a feeding sheet plus a discrete line vortex/sink. The strength of the sink is related to the entrainment of the rotational core and derived here from semi-empirical arguments. The resulting potential flow problem is solved employing a higher-order panel method which involves some recently developed ideas for obtaining a numerically efficient method with second-order accuracy. The method is applied to the calculation of the flow about a delta wing at incidence.

    Original languageEnglish
    Title of host publicationHigh Angle of Attack Aerodynamics
    Subtitle of host publicationProceedings of the AGARD Fluid Dynamics Panel Symposium, Sandeford , Norway on 4-6 October 1978,
    PublisherNational Aeronautics and Space Administration (NASA)
    Number of pages11
    Publication statusPublished - 1 Jan 2017
    EventAGARD Fluid Dynamics Panel Symposium on High Angle of Attack
    Aerodynamics 1978
    - Sandefjord, Norway
    Duration: 4 Oct 19786 Oct 1978

    Publication series

    NameAGARD Conference Proceedings
    PublisherNATO Research and Technology Agency
    Volume247
    ISSN (Print)0549-7191

    Conference

    ConferenceAGARD Fluid Dynamics Panel Symposium on High Angle of Attack
    Aerodynamics 1978
    Country/TerritoryNorway
    CitySandefjord
    Period4/10/786/10/78

    Fingerprint

    Dive into the research topics of 'Computational model for the calculation of the flow about wings with leading-edge vortices'. Together they form a unique fingerprint.

    Cite this