旋翼翼型设计是直升机旋翼设计的基础, 准确计算翼型气动特性是设计工程实用翼型的关键。在翼型的气动特性设计过程中, 使用红外成像非接触测量转捩实验技术在大型?3.2 m低速风洞中测试了OA309旋翼翼型的自由转捩位置, 采用Michel模型计算了自由转捩位置以及自由转捩对气动力的影响。通过OA309旋翼翼型的计算与实验结果对比可以看出, 计算捕捉到的转捩位置与实验结果基本一致。红外成像非接触测量转捩技术与Michel模型的联合应用提高了旋翼翼型的阻力计算精度, 为翼型多目标设计奠定了基础。

Rotor airfoil design is the foundation of helicopter rotor design, and accurate calculation of aerodynamic characteristics is the key to the design of practical engineering airfoil. In the aerodynamic characteristics design process of airfoil, the infrared imaging non-contact measurement transition test technology was used to test the free transition position of OA309 rotor airfoil in a large ?3.2 m low-speed wind tunnel, and the influence of free transition position and free transition on aerodynamic force was calculated using the Michel model. By comparing the calculation and test results of OA309 rotor airfoil, it can be seen that the transition positions captured in the calculation are basically consistent with the test results. The joint application of infrared imaging non-contact measurement transition technology and Michel model improves the calculation accuracy of rotor airfoil resistance and lays a foundation for multi-objective airfoil design.