In recent decades,PSP (Pressure Sensitive Paint )measurement technique has been improved continuously and applied to engineering wind tunnel testing of two meter scale in many aerodynamic test institutions in the world gradually,for model surface pressure measure-ment,flow visualization on model surface and CFD result validation.A binary PSP measurement system with multi light sources and CCD cameras has been established in the 2.4m transonic wind tunnel,and the many problems affecting measurement accuracy and reliability in large intermittent transonic wind tunnel tests have been solved,such as temperature changing on mod-el surface,illumination uniformity and intensity changing,model vibration,as well as test data correction,spraying and coating calibration,and so on.Meanwhile it has been employed to the surface pressure distribution measurement tests of the large aircraft model and the NASA delta wing model.Test results indicate that PSP coating has little influence on model surface pressure distribution.The difference of the root mean square of Cp between PSP and conventional pressure taps is below 0.03 under the test conditions with Mach numbers ranging from 0.4 to 1.2 and angles of attack varying from -4°to 4°,which is equal to the measurements accuracy of continu-ous transonic wind tunnel of the same scale abroad.In a word,the new PSP system and tech-nique application can provide a new advanced measurement method for the configuration optimum design of flight vehicles and aerodynamics research.%近十几年来,由于压敏漆(Pressure Sensitive Paint、PSP)测量技术的不断完善与发展,国际上主要空气动力试验机构逐步将其应用于2 m量级工程型风洞,完成模型表面压力测量、模型表面流动显示与 CFD 结果验证。在2.4m跨声速风洞建立了双组份、多光源和多CCD的PSP测量系统,解决了大型暂冲式跨超声速风洞试验存在的模型表面温度变化、光照均匀性与强度变化,以及模型振动、试验数据修正、喷涂与压敏涂料校准等诸多影响PSP测量结果精准度与可靠性的问题,并成功应用于大飞机测压模型和三角翼测压模型压力分布测量试验。试验结果表明：在小迎角范围压敏漆涂层对模型表面压力分布影响不明显；在试验马赫数0.4~0.82、模型迎角-4°~4°范围,PSP与传统电子扫描阀测量结果的Cp 均方根偏差小于0.03,测量精准度与国外同量级连续式跨声速风洞相当。可以为飞行器气动优化设计和空气动力学研究提供一种新的、先进的测试技术。
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