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Boundary layers explained: an undergraduate laboratory using an aerofoil with leadingedge slat

机译:边界层说明:使用翼缘和前缘板条的机翼的本科生实验室

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A new undergraduate laboratory exercise is described which explores the generation of lift over an aerofoil with and without a leading-edge slat. The experiment emphasises a fundamental understanding of the fluid-dynamic boundary layer and supports a second-year lecture course in fluid mechanics. A NACA 2415 aerofoil is used by the undergraduates in a simple open-return circuit wind tunnel at a Reynolds number of 2 × 10~5. Measurements of inviscid and viscous aerodynamic characteristics of the aerofoil are validated against cambered aerofoil theory and published NACA data. Oil surface-shear flow visualisation and the differences in the pressure distribution around the NACA 2415 with and without the leading-edge slat demonstrate the governing influence of the boundary layer on aerodynamic stall and the lift generated by the aerofoil. The new laboratory format was introduced to the undergraduates in 2007 and the response from student evaluation questionnaires confirmed that their understanding of basic fluid dynamics was greatly enhanced by the wind tunnel experiment.
机译:描述了一种新的本科实验室练习,该练习探索了在有和没有前沿板条的情况下,机翼上的升力的产生。该实验强调了对流体动力学边界层的基本理解,并支持了流体力学第二年课程。大学生在一个雷诺数为2×10〜5的简单开放式回路风洞中使用NACA 2415翼型。机翼的无粘性和粘性空气动力学特性的测量结果已根据弯翼机翼理论和已发布的NACA数据进行了验证。油面剪切流的可视化以及有无前缘板条的NACA 2415周围压力分布的差异证明了边界层对气动失速和由机翼产生的升力的控制影响。新的实验室形式于2007年引入大学生,学生评估调查问卷的回答证实,通过风洞实验,他们对基本流体动力学的理解大大增强了。

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