典型直升机旋翼翼型气动特性试验研究

Experimental investigation on aerodynamic performance of one typical helicopter rotor airfoil

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。

Selecting airfoils with high lift-drag ratio is the key for improving aerodynamic per- formance of helicopter rotor. The CH309 rotor airfoil was developed based on typical OA309 ro- tor 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 per- formance of CH309 airfoil is better than that of the OA309 airfoil. These experimental results are valuable for the airfoils＇ selection of designing helicopter rotor.