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 Delta Wing, and the Lockheed Martin 1021-01 configuration. A nonintrusive polynomial chaos surrogate modeling approach was used for reduced computational cost of propagating mixed, inherent (aleatory) and model-form (epistemic) uncertainty from both the computation fluid dynamics model and the near-field to ground level 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


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    West, Thomas K., IV (Autor:in) / Reuter, Bryan W. (Autor:in) / Walker, Eric L. (Autor:in) / Kleb, Bil (Autor:in) / Park, Michael A. (Autor:in)

    Kongress:

    AIAA Aviation 2014 ; 2014 ; Atlanta, GA, United States
    AIAA Applied Aerodynamics Conference ; 2014 ; Atlanta, GA, United States


    Erscheinungsdatum :

    2014-06-16


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :