不同型面组成的模型机翼气动特性和气动性能的研究

A. Askan, S. Tangöz, M. Konar
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引用次数: 0

摘要

在2 × 105雷诺数(Re)和从- 4°到最大升力点的不同迎角范围内,研究了波音737-Classic型飞机机翼的气动性能和分离特性,以及由这些翼型组成的模型机翼。实验在埃尔西耶斯大学航空航天学院气动实验室的低速风洞中进行。四种型材组合后得到的模型翼呈矩形,尺寸为0.21m × 0.21m。在这个由两部分组成的研究的第一部分中,分别检查了机翼的气动性能和流动分离。在研究的第二阶段,研究了模型机翼的气动性能和流动分离行为,并将结果与每个剖面的数据进行了比较。研究结果表明,数值图形的斜率与实验结果基本吻合。在迎角(AoA)为20°之前,压力和速度分布基本符合正常趋势。相反,在这个角度以上的剖面上出现了负速度值和负压区。空气在翼型和模型翼上以层流形式流动至20°,在AoA约24°处开始出现层流分离气泡。最后,该模型翼获得了最佳的气动性能。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
An investigation of aerodynamic behaviours and aerodynamic performance of a model wing formed from different profiles
In this study, the aerodynamic performances and the flow separation behaviour of the wing profiles, used in the wing of Boeing 737-Classic aircraft, and a model wing formed of these profiles were investigated at 2 × 105 Reynolds number (Re) and different angles of attack ranging from −4° to the angle, which maximum lift point obtained. The experiments were conducted in a low-speed wind tunnel in Erciyes University Faculty of Aeronautics and Astronautics Aerodynamic Laboratory. Four profiles and the model wing, which was obtained from the combination of the four profiles were produced in a rectangular shape with dimensions of 0.21m × 0.21m. In the first part of this two-part study, the wing profiles were examined individually regarding aerodynamic performance and flow separation. In the second phase of the study, the aerodynamic performance and the flow separation behaviour of the model wing were examined and the results were compared with the data obtained from each profile. The study results showed that the slopes of the numerical graphics are generally quite consistent with experimental results. In addition, the pressure and velocity distributions have followed the normal trend until the angle-of-attack (AoA) of 20°. In contrast, the negative speed values and negative pressure zones have appeared on the profile above this angle. The air flowed as laminar on the profiles and the model wing until 20°, while laminar separation bubbles are begun to take place at about 24° AoA. Finally, the best aerodynamic performance has been obtained with the model wing.
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