Steady lifting flows over highly swept delta wings at large incidence were studied. After an exhaustive literature review, development of a vortex-lattice method was attempted. To demonstrate the feasibility of using such a method, an existing code was modified. A system of vortex lines to simulate the leading-edge wake was added. The coefficients predicted by the modified code were in good agreement with experimental data.


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    Title :

    Subsonic steady and unsteady aerodynamic loads on missiles and aircraft


    Publication date :

    1983-01-18


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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