【摘要】 采用高升阻比特性的翼型是提高直升机旋翼气动性能的关键。对在典型的OA309旋翼翼型基础上开发的CH309翼型,进行了低、高速气动特性风洞试验研究。试验分别在FL-14风洞和NF-6风洞中进行,采用表面测压和尾耙型阻测量技术。试验结果表明:CH309翼型的总体性能优于OA309翼型。试验结果为直升机旋翼设计时翼型的选取提供了参考。更多还原

【Abstract】 Selecting airfoils with high lift-drag ratio is the key for improving aerodynamic performance of helicopter rotor.The CH309 rotor airfoil was developed based on typical OA309 rotor airfoil,and the experimental investigation on low and high speed aerodynamic performance was made.The tests were performed in a two-dimensional testing section of FL-14 wind tunnel at China Aerodynamics Research and Development Center and NF-6 wind tunnel at Northwestern Polytechnical University respectively.Surface pressure measurement and drag measurement with trail total pressure row tube were carried out.Experimental results show that the overall performance of CH309 airfoil is better than that of the OA309 airfoil.These experimental results are valuable for the airfoils′ selection of designing helicopter rotor.更多还原