The DLR inverse design code computes the wing geometry for a prescribed target pressure distribution. It is based on the numerical solution of the integral inverse transonic small perturbation (TSP) equations. In this work, several extensions and modifications of the inverse design code are described. Results are validated with corresponding redesign test cases. The first modification concerns applications for high transonic Mach numbers or cases with strong shocks. The introduced modifications enable converged design solutions for cases where the original method failed. The second modification is the extension of the code to general non-planar wings. Previously, the design code was restricted to non-planar wing designs with small dihedral or to nacelle design. A third modification concerns aerofoil/wings designed for wind-tunnel design. In order to design a swept wing between two wind-tunnel walls, the solution method was extended to two symmetry planes. The introduced extensions and modifications have increased the robustness and range of applicability of the inverse design code.


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    Titel :

    DLR transonic inverse design code, extensions and modifications to increase versatility and robustness


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 55.50
    Lokalklassifikation TIB:    275/7040



    Transonic airfoil design code

    Bauer, F. / Garabedian, P. / Korn, D. | NTRS | 1980



    Inverse Transonic Wing Design Method

    P. A. Henne | AIAA | 1981



    Transonic computational design modifications of the F-111 TACT

    CHEN, A. / TINOCO, E. / YOSHIHARA, H. | AIAA | 1978