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.
Shock-Dependent, Optimum Thrust Wings in Supersonic Flow
1992
141 pages
Report
Keine Angabe
Englisch
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