旋翼翼型高速风洞动态试验装置研制

为弥补国内在旋翼翼型高速风洞动态试验模拟能力和测试精度方面的不足，基于FL-20连续式跨音速风洞，提出采用双端同步驱动旋翼翼型试验模型的方式，设计了一套高速风洞动态试验装置。该装置依托双天平动态载荷测量结合表面动态压力测量的方式，可提高旋翼翼型动态气动载荷的测量精度。风洞试验结果显示：当旋翼翼型试验模型的俯仰振荡幅值为10°时，其振荡频率可达17 Hz，且试验马赫数为0.6，雷诺数达到5×10⁶，处于国际领先水平。所研制的动态试验装置及其相关测试技术具有较高的可靠性，且试验数据可靠、规律合理，具备了开展高速风洞动态试验的能力，可为旋翼翼型动态失速问题的研究以及真实直升机试验参数的模拟提供重要的技术支撑。

Development of dynamic test equipment for rotor airfoil in high speed wind tunnel

In order to make up for the deficiency of simulation ability and test accuracy of rotor airfoil dynamic test in high speed wind tunnel at domestic, based on the FL-20 continuous transonic wind tunnel, a method of dual-end synchronous driving rotor airfoil test model was proposed, and a dynamic test equipment for the high speed wind tunnel was designed. The equipment relied on the way of dual-balance dynamic load measurement combined with surface dynamic pressure measurement, which could improve the dynamic aerodynamic load measurement accuracy of rotor airfoil. The wind tunnel test results showed that: when the pitch oscillation amplitude of rotor airfoil test model was 10°, its oscillation frequency could reach 17 Hz, the test Mach number was 0.6, and the Reynolds number was 5×10⁶, which was at the international leading level. The developed dynamic test equipment and its related test technology have high reliability, and the test data is reliable and its law is reasonable, which has the ability to carry out high speed wind tunnel dynamic test. It can provide important technical support for the research of rotor airfoil dynamic stall and the simulation of real helicopter test parameters.