The conservative, unsteady Euler equations for the flow relative to a moving frame of reference are used to solve for the three-dimensional steady and unsteady flows around a sharp-edged delta wing. The resulting equations are solved by using an implicit, approximately factored, finite-volume scheme. Implicit second-order and explicit second- and fourth-order dissipations are added to the scheme. The boundary conditions are explicitly satisfied. The grid is generated by locally using a modified Joukowski transformation in crossflow planes at the grid-chord stations. The computational applications cover a steady flow around a delta wing, whose results serve as the initial conditions for the unsteady flow around a pitching delta wing at a large mean angle of attack. The steady results are compared with the experimental data, and the unsteady results are compared with results of a flux-difference splitting scheme.


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    Title :

    Computation of vortex-dominated flow for a delta wing undergoing pitching oscillation


    Contributors:

    Published in:

    Publication date :

    1990-09-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :




    Vortex Breakdown over a Pitching Delta Wing

    Gursul, I. / Yang, H. / AIAA | British Library Conference Proceedings | 1994


    Vortex breakdown over a pitching delta wing

    Gursul, Ismet / Yang, Houbin | AIAA | 1994


    Vortex Breakdown Over a Pitching Delta Wing

    Gursel, I. / Yang, H. / AIAA | British Library Conference Proceedings | 1994