基于0.6 m量级三声速风洞的压敏漆试验技术

基于0.6 m暂冲式三声速风洞，建立了压敏漆测压系统，解决了各分系统的同步控制问题。研究了涂料喷涂影响、图像滤波和系统测量稳定性及精准度等技术细节，并将该系统首次应用于未来大型客机减阻与激波控制的机翼表面压力测量中，获得了基本外形和鼓包外形机翼表面的压力分布、激波位置及形态。检验了设计鼓包在设计状态和稍偏离设计状态下的激波控制效果及其对上翼面压力分布和升力特性的影响。研究结果表明：涂料喷涂质量不佳造成的表面粗糙度和厚度变化会显著影响压力分布，喷涂质量需严格控制。窗口直径8像素迭代3次的高斯滤波对压力波动的平滑效果较好且不会失真。建立的压敏漆系统与压力传感器的压力系数测量均方根偏差在0.022以内，压力均方根偏差小于620 Pa，测量精准度较高。设计鼓包在设计状态及稍偏离设计状态下，均能够有效减弱激波强度，保证机翼升力变化很小，从而提高机翼的升阻比。

Experimental technique of pressure sensitive paint based on 0.6 m trisonic wind tunnel

A pressure-sensitive paint measurement system is established in a 0.6 m trisonic wind tunnel to resolve the subsystem synchronization control problem. Based on the established pressure-sensitive paint system, this research studies the effect of coating on the surface pressure distribution as well as the image filtering technology and the measurement stability and accuracy of the pressure-sensitive paint system. The system is applied for the first time to the wing surface pressure measurement test in future large passenger aircraft drag reduction and shock control, obtaining the pressure distribution and the shock position of the original wing and the bump wing on the wing upper surface. Then the design of bump is verified to have a good shock control effect in the design state. The results indicate that the changes in surface roughness and thickness caused by low coating quality can significantly affect the pressure distribution, necessitating the need of strict control of the spray quality. In addition, Gaussian filtering with 8-pixel windows and 3-time iterations presents better smoothing of pressure fluctuations without distortion. The pressure coefficient measurement root mean square deviation between the established pressure-sensitive paint system and the pressure sensor is smaller than 0.022,the root mean square deviation of pressure is less than 620 Pa,revealing high measurement accuracy of the pressure-sensitive paint system. Furthermore, the design bump can effectively weaken the shock wave and improve the lift and drag characteristics of the wing in both the design state and non-design state.