A static aeroelastic analysis capability that can calculate flexible air loads for generic configuration aircraft 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 is computed externally and inserted in the NASTRAN by means of a DMAP program. It was shown that deformation and flexible airloads of an oblique wing aircraft can be calculated reliably by this code both in subsonic and supersonic speeds. Preliminary results indicating importance of flexibility in calculating air loads for this type of aircraft are presented.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Static Aeroelastic Analysis for Generic Configuration Aircraft


    Beteiligte:
    I. Lee (Autor:in) / H. Miura (Autor:in) / M. K. Chargin (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    53 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Static aeroelastic analysis for generic configuration aircraft

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


    Static aeroelastic analysis for generic configuration wing

    Lee, IN / Miura, Hirokazu / Chargin, Mladen K. | NTRS | 1991


    Static aeroelastic analysis for generic configuration wing

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