A computational method for predicting the aerodynamic performance of a vertical tail due to active flow control has been developed. Enhanced directional control using flow-control technology can potentially result in reduced fuel consumption and improved airplane performance. The numerical method is based on the unsteady Reynolds-averaged Navier–Stokes formulation for overset grid systems. The flow control is modeled for an array of synthetic jet actuators mounted at the trailing edge of the stabilizer. Results of the validation for various flow conditions, actuation parameters, and port layouts are used to establish the accuracy of the numerical tool. The side-force increments on the tail due to flow control at various sideslip conditions are presented. Sensitivities to flow-control layouts, especially with respect to spanwise flow development, are also investigated. A practical approach to facilitate preliminary evaluations of active flow control with quick computational turnaround is proposed. It is shown that constant actuation can be used as proxy for predicting the effects of the unsteady actuation from synthetic jets. Its confirmation in the context of the current application has been invaluable for developing practical flow-control implementations. Aspects of integration are presented, and guidelines for preferred modes of actuation are put forth.


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    Title :

    Computational Evaluation of Flow Control for Enhanced Control Authority of a Vertical Tail



    Published in:

    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040



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