A static aeroelastic analysis capability that calculates flexible air loads for generic configuration wings was developed. It was made possible by integrating a finite element structural analysis code (MSC/NASTRAN) and a panel code of aerodynamic analysis based on linear potential flow theory. The framework already built in MSC/NASTRAN was used, and the aerodynamic influence coefficient matrix was computed externally and inserted in the NASTRAN by means of a DMAP program. It was shown that deformation and flexible air loads of an oblique wing configuration including asymmetric wings can be calculated reliably by this code both in subsonic and supersonic speeds.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Static aeroelastic analysis for generic configuration wing


    Beteiligte:
    Lee, IN (Autor:in) / Miura, Hirokazu (Autor:in) / Chargin, Mladen K. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1991



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Static aeroelastic analysis for generic configuration wing

    LEE, IN / MIURA, HIROKAZU / CHARGIN, MLADEN K. | AIAA | 1991


    Static Aeroelastic Analysis for Generic Configuration Aircraft

    I. Lee / H. Miura / M. K. Chargin | NTIS | 1987


    Static aeroelastic analysis for generic configuration aircraft

    Lee, IN / Miura, Hirokazu / Chargin, Mladen K. | NTRS | 1987


    Static aeroelastic analysis of a three-dimensional generic wing

    Green, John A. / Lee, IN / Miura, Hirokazu | NTRS | 1990


    Static Aeroelastic Analysis of a Three-Dimensional Generic Wing

    J. A. Green / I. Lee / H. Miura | NTIS | 1990