A study has been conducted on a conical wing-body transatmospheric vehicle at Mach numbers from 1.5 to 4.5. The objective of the study was to evaluate the application of a Euler code to a wing-body configuration across the supersonic Mach number range. The baseline wing-body fuselage consisted of a circular 5-deg half-angle conical forebody, a cylindrical midbody, and a 9-deg truncated conical boattail. The wing was a 4-percent-thick diamond airfoil wing of aspect ratio 1. Results show that the Euler code accurately predicted the lift, drag, and pitching moment coefficients as a function of Mach number and angle of attack. The longitudinal stability characteristics were predicted as a function of Mach number. The code also predicted the changes in lift, drag, and pitching moment for forward and rearward shift of the wing from the nominal position.


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    Title :

    Euler code evaluation of a conical vehicle at supersonic speeds


    Contributors:

    Publication date :

    1989-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Euler code evaluation of a conical vehicle at supersonic speeds

    MCGRATH, BRIAN / WALKER, IRA / COVELL, PETER | AIAA | 1989


    Euler code evaluation of a transatmospheric vehicle at supersonic speeds

    Mcgrath, Brian E. / Walker, Ira J. / Covell, Peter F. et al. | NTRS | 1991


    Euler code evaluation of a transatmospheric vehicle at supersonic speeds

    MCGRATH, BRIAN E. / WALKER, IRA J. / COVELL, PETER F. et al. | AIAA | 1991