デルタ翼後縁ジェットによる揚力増加

概要

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The subsonic flow for a 45deg-swept delta wing is numerically simulated to see the effects of trailing edge jet on aerodynamic forces. Computation has been performed at an angle of attack of 20deg and a Reynolds number of 2.0×104 based on the wing root chord. Under these conditions, the flow is fully separated from the wing surface, so that no suction peaks due to leading edge vortices appear over the upper surface of the wing. Consequently, the delta wing cannot take advantage of a vortical lift. When a jet is emitted normal to the wing lower surface near the trailing edge, the flow along the wing lower surface is decelerated. That is, the circulation around the wing increases. In one of the cases studied here, the lift coefficient became more than 40% higher than that of the plain delta wing. By contrast, in the case of trailing edge jet parallel to the wing lower surface, the flow along the wing lower surface is accelerated, and the lift coefficient became lower than that of the plain delta wing.
社団法人日本航空宇宙学会の論文
2004-03-05