Prediction of the loss of wing leading-edge thrust and the accompanying increase in drag due to lift, when flow is not completely attached, presents a difficult but commonly encountered problem. A method (called the previous method) for the prediction of attainable leading-edge thrust and the resultant effect on airplane aerodynamic performance has been in use for more than a decade. Recently, the method has been revised to enhance its applicability to current airplane design and evaluation problems. The improved method (called the present method) provides for a greater range of airfoil shapes from very sharp to very blunt leading edges. It is also based on a wider range of Reynolds numbers than was available for the previous method. The present method, when employed in computer codes for aerodynamic analysis, generally results in improved correlation with experimental wing-body axial-force data and provides reasonable estimates of the measured drag.


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    Title :

    Improved Method for Prediction of Attainable Wing Leading-Edge Thrust



    Publication date :

    1996-04-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Wing design with attainable leading-edge thrust considerations

    CARLSON, H. W. / SHROUT, B.L. / DARDEN, C. M. | AIAA | 1985


    Wing design with attainable leading-edge thrust considerations

    Carlson, H. W. / Shrout, B. L. / Darden, C. M. | NTRS | 1985


    Wing design with attainable thrust considerations

    Carlson, H. W. / Shrout, B. L. / Darden, C. M. | NTRS | 1984


    Wing design with attainable thrust considerations

    CARLSON, H. / SHROUT, B.L. / DARDEN, C. | AIAA | 1984