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Experimental aerodynamics of delta wing mini UAVs and their scaling

机译：三角翼迷你无人机的实验空气动力学及其缩放

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This paper describes experimental aerodynamics of remotely controlled delta wing mini UAV prototypes (empty weight ca. 100g, payload 70g, wing span ca. 500mm) with a view to scaling down the design to the micro UAV size. Flight tests of one prototype revealed unexpectedly low performance, in particular a low gliding ratio and poor elevon's effectiveness. Wind tunnel tests were performed to elucidate the reasons for this behaviour using the following five models: Model A - typical all wing configuration with thick aerofoils (good performance in flight tests); Model B - delta wing configuration with thick aerofoils (low performance in flight tests); Model C - all wing configuration and thin aerofoils; Model D - delta wing configuration and thin aerofoils; Model E - delta wing configuration and modified thin aerofoils. Of particular interest is the "mid span vortex" discovered on model B which seems to be specific to low Reynolds numbers aerodynamics. It was probably responsible for low performance results in flight tests of this model. Wind tunnel tests of models A, C, D and E seem to suggest some methods to overcome this problem. They are analysed at the end of the paper.
机译：本文介绍了远程控制的Delta Wing Mini UAV原型的实验空气动力学（空体重CA.100G，有效载荷70G，翼跨度CA. 500mm），以便将设计缩小到微无人机尺寸。一个原型的飞行测试揭示了出乎意料的低性能，特别是较低的滑翔比和差的高度的有效性。进行风洞测试以阐明使用以下五种型号的这种行为的原因：模型A - 典型的所有机翼配置，具有厚的翼型（飞行试验中的良好性能）;模型B - Delta翼式配置，具有厚的机翼机（飞行试验性能低）;模型C - 所有翼配置和薄机翼;模型D - Delta翼配置和薄机翼;型号E - Delta翼配置和改装薄机翼。特别感兴趣的是在模型B上发现的“Mid Span Vortex”，它似乎特定于低雷诺数空气动力学。这可能对该模型的飞行测试中的低效结果负责。模型A，C，D和E的风洞测试似乎有一些方法来克服这个问题。它们在纸张结束时分析。

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