| 摘要 |
PCT No. PCT/GB87/00320 Sec. 371 Date Jan. 12, 1989 Sec. 102(e) Date Jan. 12, 1989 PCT Filed May 12, 1987 PCT Pub. No. WO87/06908 PCT Pub. Date Nov. 19, 1987.In modern thin wing aircraft flow separation at high incidence may originate at the leading edge. This invention combats the problem by restricting the growth of the region of separated flow by re-energizing the boundary flow downstream of reattachment line (7). It utilizes upper surface grooves (8 and 9) extending rearwardly from the leading edge (5) of the wing. The grooves (8 and 9) have a width at opening in the range 0.05 to 1.0 percent of the aerofoil span and length in the range 1 to 20 percent of the local chord length. Spanwise flow across the grooves causes vortex formation which produces the desired effect without significant drag penalty. In swept wings the grooves are parallel to chord. In straight or forward swept wings the grooves are inclined. The wing includes several grooves each acting as a barrier to growth of flow separation until swallowed within the separated flow.
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