A new wing concept that reduces the inviscid drag of a wing in supersonic flow is presented. This wing concept utilizes a secondary shock that occurs aft of the maximum thickness location to produce a significant aerodynamic thrust force from the aft portion of the wing, thereby reducing the inviscid drag. The increased aft-wing thrust force is created by contouring each streamwise airfoil aft of the maximum thickness location to obtain a more favorable orientation of the local wing surface. The aerodynamic thrust force has generally been associated with the near leading-edge region of a wing previously. The secondary shock is clearly identified and favorably exploited herein for the first time.


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    Title :

    Shock-Dependent, Optimum Thrust Wings in Supersonic Flow


    Contributors:

    Publication date :

    1992


    Size :

    141 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Supersonic Wings with Significant Leading-Edge Thrust at Cruise

    A. W. Robins / H. W. Carlson / R. J. Mack | NTIS | 1980


    Supersonic wings with significant leading-edge thrust at cruise

    Robins, A. W. / Carlson, H. W. / Mack, R. J. | NTRS | 1980