Aerodynamic Characteristics of Finite Span Wings with Leading-Edge Protuberances
Aerodynamic Characteristics of Finite Span Wings with Leading-Edge Protuberances
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DOI：
10.2514/1.j053568
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发表时间：
2015-02
期刊：
影响因子：
2.5
通讯作者：
D. Custodio;C. Henoch;H. Johari
中科院分区：
文献类型：
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作者：
D. Custodio;C. Henoch;H. Johari
进行了一系列水洞实验，以确定正弦前缘突起对有限展弦比机翼气动特性的影响。模型包括七个矩形平面形状的机翼、两个后掠前缘机翼以及两个平面形状类似座头鲸鳍状肢的机翼。所有模型都基于NACA 634 - 021翼型，突起幅度为弦长的0.025 - 0.12倍。在雷诺数高达4.5×10⁵以及攻角高达30度的条件下对模型进行了测试。在雷诺数高于3.6×10⁵时，升力系数和阻力系数几乎与雷诺数无关。与基准模型相比，特定的矩形平面形状模型在有限的攻角范围内具有明显更大的升力系数。然而，除了类似座头鲸鳍状肢的平面形状外，所有前缘修改模型的升阻比与等效基准模型相当或更低。鳍状肢模型有轻微的……
A series of water-tunnel experiments were conducted to determine the effect of sinusoidal leading-edge protuberances on the aerodynamic characteristics of finite span wings. The models consisted of seven rectangular planform wings, two swept-leading-edge wings, and two wings with a planform resembling humpback-whale flippers. All models had an underlying NACA 634-021 profile with protuberance amplitudes of 0.025–0.12 times the chord length. The models were examined at Reynolds numbers up to 4.5×105 and angles of attack up to 30 deg. The lift and drag coefficients were nearly independent of Reynolds numbers above 3.6×105. Specific rectangular-planform models had appreciably greater lift coefficients over a limited angle-of-attack range when compared to the baseline model. However, with the exception of the planform that resembled the humpback-whale flipper, the lift-to-drag ratio of all leading-edge modified models was comparable to or less than the equivalent baseline model. The flipper model had a slight...