Three-dimensional viscous flow computations are presented for the F/A-18 forebody including the leading-edge extension geometry. Solutions are obtained from an algorithm for the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-difference-splitting approach along with longitudinally patched grids. Results are presented for both laminar and fully turbulent flow assumptions and include correlations with wind-tunnel as well as flight-test results. A good quantitative agreement for the forebody surface pressure distribution is achieved between the turbulent computations and wind-tunnel measurements at M = 0.6. The computed turbulent surface flow patterns on the forebody qualitatively agree well with in-flight surface flow patterns obtained on an F/A-18 aircraft at M = 0.34


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Navier-Stokes Solutions About the F/A-18 Forebody-Leading-Edge Extension Configuration


    Contributors:

    Conference:

    27th Aerospace Sciences Meeting ; 1989 ; Reno, NV, US


    Published in:

    Publication date :

    1990-09-01




    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Navier-Stokes solutions about the F/A-18 forebody-leading-edge extension configuration

    GHAFFARI, FARHAD / LUCKRING, JAMES M. / THOMAS, JAMES L. et al. | AIAA | 1990


    Navier-Stokes solutions about the F/A-18 forebody-LEX configuration

    GHAFFARI, FARHAD / BATES, BRENT / LUCKRING, JAMES et al. | AIAA | 1989




    Application of a Patched-Grid Algorithm to the F/A-18 Forebody-Leading-Edge Extension Configuration

    James L Thomas / Robert W. Walters / Taekyu Reu et al. | NTRS | 1990