Wind tunnel tests were conducted to investigate the aerodynamic characteristics of an SST model with leading-edge and trailing-edge flaps. Force measurement and surface pressure measurement were performed for the SST model with leading-edge flaps or with trailing-edge flaps and with both flaps deflected. Flow patterns on the upper surface of the model were visualized by means of oil-flow and smoke. Lift-to-drag ratio of the model was improved by leading-edge flap deflection. Deflecting the trailing edge flap increased lift, drag and pitch-down moment drastically. When the trailing-edge flap was deflected to ten degrees, lift-to-drag ratio could also be improved. The combined effects of leading-edge and trailing-edge flaps were discussed by comparison with the linearly combined measurement results when the leading-edge and trailing-edge flaps were deflected separately.


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    Titel :

    Technical Report of National Aerospace Laboratory. Experimental Investigation of High Lift Device for SST


    Beteiligte:
    D. Y. Kwak (Autor:in) / K. Miyata (Autor:in) / M. Noguchi (Autor:in) / Y. Sunada (Autor:in) / K. Rinoie (Autor:in)

    Erscheinungsdatum :

    2002


    Format / Umfang :

    42 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch