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首页> 外文期刊>Journal of Aircraft >Studies on Vortex Flaps with Rounded Leading Edges for Supersonic Transport Configuration
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Studies on Vortex Flaps with Rounded Leading Edges for Supersonic Transport Configuration

机译：超音速运输配置中具有圆形前缘的涡瓣的研究

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Wind-tunnel measurements were taken on a cranked arrow wing supersonic transport configuration with leading-edge vortex flaps. Force and surface pressure measurements were made at Reynolds number based on the wing mean aerodynamic chord from 9.2 x 10~5 to 3.8 x 10~6. Two different flap cross sections (the originally designed nonrounded leading edge and the rounded leading edge) were tested. The purpose of the measurements is to clarify how the differences of the Reynolds number affect the flow around the rounded leading-edge vortex flaps and the flap performance. The wing with the rounded leading-edge vortex flaps indicated some benefit of the lift/drag ratio as compared with those of the nonrounded vortex flaps at a relatively high-lift coefficient greater than 0.3. Different flow patterns were observed over the rounded leading-edge vortex flaps when the Reynolds number was increased at a lift coefficient greater than 0.5. The spanwise length of the separated region shortens as the Reynolds number is increased.
机译：风洞测量是在带有前涡旋襟翼的曲柄箭翼超音速运输配置上进行的。力和表面压力的测量基于机翼平均空气动力弦从9.2 x 10〜5到3.8 x 10〜6的雷诺数进行。测试了两个不同的襟翼横截面（最初设计的非圆形前缘和圆形前缘）。测量的目的是阐明雷诺数的差异如何影响圆形前缘涡旋襟翼周围的流动和襟翼性能。相对于不大于0.3的较高升力系数，带有圆形前缘涡流襟翼的机翼与非圆形涡流襟翼相比具有升力/阻力比的某些优势。当雷诺数在升力系数大于0.5时增加时，在圆形前缘涡旋襟翼上观察到不同的流动模式。随着雷诺数的增加，分离区域的翼展方向长度会缩短。

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