The primary objective of this work was to develop and demonstrate a process for accurate and efficient uncertainty quantification and certification prediction of low-boom, supersonic, transport aircraft. High-fidelity computational-fluid-dynamics models of multiple low-boom configurations were investigated, including the Lockheed Martin SEEB-ALR body of revolution, the NASA 69 deg delta wing, and the Lockheed Martin 1021-01 configuration. A nonintrusive polynomial chaos surrogate approach was used for reduced computational cost of propagating mixed inherent (aleatory) and epistemic uncertainty through both the computational-fluid-dynamics model and the near-field to ground-level boom propagation model. A methodology has also been introduced to quantify the plausibility of a design to pass a certification under uncertainty. Results of this study include the analysis of each of the three configurations of interest under inviscid and fully turbulent flow assumptions. A comparison of the uncertainty outputs and sensitivity analyses between the configurations is also given. The results of this study illustrate the flexibility and robustness of the developed framework as a tool for uncertainty quantification and certification prediction of low-boom, supersonic aircraft.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Uncertainty Quantification and Certification Prediction of Low-Boom Supersonic Aircraft Configurations



    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Lokalklassifikation TIB:    770/7040