Several questions relevant to the feasibility of achieving successful VTOL flight with thrust agumenting ejector wings are answered by the present experimental study. Tests were performed with a large-scale turbofan powered augmentor that embodied many of the problems encountered in the design of real flight hardware. The apparatus consisted of four separate and parallel ejector channels in each of two wings. Results were compared with data from other laboratory experiments using a single channel ejector of similar geometry. Over-all performance levels of the large multichannel apparatus correlated well with the single-channel results. Minor interactions between the four ejector channels on each wing had no significant effect on the over-all level of thrust augmentation. However, the distribution of thrust was affected and should be considered in future aircraft system designs. Operating as an air pump, the turbofan engine was maintained in its safe operating regime throughout all test configurations. (Author)


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    Titel :

    Test Results of a VTOL Propulsion Concept Utilizing a Turbofan Powered Augmentor


    Beteiligte:
    D. R. Campbell (Autor:in) / B. Quinn (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    7 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Full-scale tests of an augmentor VTOL concept

    CAMPBELL, D. / QUINN, B. | AIAA | 1973


    VTOL turbofan test-bed

    Engineering Index Backfile | 1963


    VTOL turbofan test-bed

    Engineering Index Backfile | 1963


    VTOL turbofan test-bed

    Engineering Index Backfile | 1963