A low-speed experimental investigation detailing the design and evaluation of a self-contained circulation-control wing is presented. A moderate aspect-ratio wing (3.34) utilizing a low-Reynolds-number S8036 profile was tested at R e = 170 , 000 . The trailing-edge jet was produced using two internal impellers drawing air off the wing tips. The effect of trailing-edge bluntness was examined as was the jet’s quiescent characteristics. Achievable jet-momentum coefficients were low, limiting circulation control to the boundary-layer control regime. Force-balance testing indicated that the circulation-control system could achieve a moderate zero-lift angle-of-attack shift; however, the primary effect of the jet was flow control at high incidence, in which stall was delayed significantly. The blunt trailing edge (Coanda surface) caused a significant increase in the minimum drag coefficient, reducing both the range and endurance parameters.


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    Title :

    Experimental Evaluation of a Self-Contained Circulation-Control Wing


    Contributors:

    Published in:

    Journal of Aircraft ; 50 , 3 ; 764-777


    Publication date :

    2013-04-08


    Size :

    14 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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