Experimental and numerical results of a propeller of 0.3 m diameter operated at 5000 RPM and axial velocity ranging from 0 to 20 m/s and advance ratio ranging from 0 to 0.8 are presented as a preliminary step towards the definition of a benchmark configuration for low Reynolds number propeller aeroacoustics. The corresponding rotational tip Mach number is 0.23 and the Reynolds number based on the blade sectional chord and flow velocity varies from about 46000 to 106000 in the operational domain and in the 30% to 100% blade radial range. Force and noise measurements carried out in a low-speed semi-anechoic wind-tunnel are compared to scale-resolved CFD and low-fidelity numerical predictions. Results identify the experimental and numerical challenges of the benchmark and the relevance of fundamental research questions related to transition and other low Reynolds number effects.

介绍了直径为0.3 m的螺旋桨的实验和数值结果，转速为5000 RPM，轴向速度为0至20 m / s，推进比为0至0.8，这是迈向确定低雷诺基准结构的第一步数字螺旋桨航空声学。相应的旋转尖端马赫数为0.23，基于叶片截面弦和流速的雷诺数在工作范围内以及叶片径向范围为30％至100％的范围内约为46000到106000。将在低速半消声风洞中进行的力和噪声测量结果与比例解析CFD和低保真度数值预测进行了比较。