A numerical method has been developed to compute transonic flows about realistic wing-fuselage configurations. The finite difference scheme employs an improved small disturbance flow equation. A unique grid embedding technique, which was heretofore applied to airfoils and wings, has been extended to include the treatment of both body and wing-body shapes. The resulting high-density mesh is shown to be a valuable asset in resolving details of the three-dimensional flow. A mathematical modeling system is used to process arbitrary fuselage geometries for body boundary conditions. Correlations with experimental data for simple isolated bodies, an isolated fuselage, and wing-fuselage combinations are included.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Computational transonic flow about realistic aircraft configurations


    Beteiligte:
    Boppe, C. W. (Autor:in)

    Kongress:

    Aerospace Sciences Meeting ; 1978 ; Huntsville, AL


    Erscheinungsdatum :

    01.01.1978


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




    Unsteady transonic flow calculations for realistic aircraft configurations

    Batina, John T. / Seidel, David A. / Bland, Samuel R. et al. | NTRS | 1987


    Unsteady transonic flow calculations for realistic aircraft configurations

    BATINA, JOHN T. / SEIDEL, DAVID A. / BLAND, SAMUEL R. et al. | AIAA | 1989


    Unsteady transonic flow calculations for realistic aircraft configurations

    Batina, John T. / Seidel, David A. / Bland, Samuel R. et al. | NTRS | 1987