A program to calculate the aerodynamic loading of supersonic airplanes, using the transonic small perturbation potential method is described. A version to allow for two wing surfaces with wakes was developed. The wing deformations are assumed to be linear functions of the load distributions. The iterative procedure used to solve the transonic small perturbation potential equation in finite difference form can treat the flow field around given wing shapes. As the shape of elastic wings is, a priori, not known temporary wing shapes must be determined. These depend on temporary load distributions and are quantified through the deformation matrix of the wing. When external aerodynamic loads are in equilibrium with internal elastic forces the final shape of the wing is obtained.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Description of a Computer Program Treating Transonic Steady State Aeroelastic Effects for a Canard or Tail Airplane


    Beteiligte:
    N. Agrell (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    28 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch