Abstract
The wave drag is an important factor that affects the supersonic flight efficiency and is closely related to the aircraft’s cross-sectional area distribution. A reasonable cross-sectional area distribution determines supersonic aircraft wave drag reduction. In this paper, an exploration of the supersonic aircraft wing–body shape parameterization using the class-shape-refinement-transformation technique and the method of extended far-field composite-element (EFCE) supersonic wing–body wave drag optimization are proposed. The method was applied to a supersonic civil transport wing–body shape optimization, yielding a 40.5% reduction of wave drag coefficient. In this way, the goal of reducing the wave drag in sufficient precision without any lift penalty was achieved. The EFCE wave drag optimization method is available in the conceptual design process of supersonic cruise aircraft to achieve high lift-to-drag ratio characteristics in supersonic flight conditions.
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