The invention relates to a film drag reduction mechanism suitable for an airplane body. The thin film drag reduction mechanism comprises a substrate layer and a thin film layer. The bottom surface ofthe base layer can be tiled and fixed on an equal straight section of an airplane. The thin film layer is located on the top face of the base layer, a plurality of ribs are formed on the outward surface of the thin film layer and are parallel to one another, and the rib thin film drag reduction mechanism is provided with a triangular cross section, wherein the included angle theta between the extending direction of the ribs and the incoming flow direction of the airplane when the airplane flies sideslip at the attack angle of 0 degree, and theta is larger than or equal to 0 degree and smallerthan or equal to 10 degrees.
本发明涉及一种适用于飞机机身的薄膜减阻机构。该薄膜减阻机构包括基底层和薄膜层。其中所述基底层的底面能够平铺固定在所述飞机的等直段。薄膜层位于基底层的顶面,且薄膜层的朝外表面形成多条肋条,多条所述肋条彼此平行,所述肋条薄膜减阻机构具有三角形横截面;其中,所述肋条的延伸方向与所述飞机以0°攻角0°侧滑飞行时的来流方向之间的夹角θ为:0°≤θ≤10°。
Film drag reduction mechanism suitable for airplane body
一种适用于飞机机身的薄膜减阻机构
2020-12-04
Patent
Elektronische Ressource
Chinesisch
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