基于曲面样条插值的压力敏感涂料测压数据修正方法  

Pressure sensitive paint measurement correction method based on surface spline interpolation

作　　者：荆志伟[1] 王立波[1] 唐矗 JING Zhiwei;WANG Libo;TANG Chu(The First Aircraft Institute,Aviation Industry Corporation of China,Ltd.,Xi'an 710089,China;Unmanned System Research Institute,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]中国航空工业集团公司第一飞机设计研究院,西安710089 [2]西北工业大学无人系统技术研究院,西安710072

出　　处：《实验流体力学》2023年第6期112-119,共8页Journal of Experiments in Fluid Mechanics

摘　　要：压力敏感涂料(Pressure Sensitive Paint,PSP)试验结果修正方法多基于最小二乘法实现,通常忽视了翼面上弦向和展向的流动特性。利用无限平板样条(Infinite Plate Spline,IPS)插值技术,建立了适用于压力敏感涂料试验结果修正的混合修正方法与流程。使用传统测压试验的全展长飞机模型,在2.4 m量级跨声速风洞中同时开展了完整机翼的PSP测压和PSI(Pressure Scanner Instrument)测压试验,试验马赫数为0.735,迎角范围为-6.38°~10.59°。试验结果与修正结果表明:PSP试验结果与PSI试验结果整体吻合较好,但PSP试验系统对机翼前缘流场捕获精度较差;混合修正方法有效,且兼顾了翼面前缘、中部和后缘的压强分布特点,修正后的压强分布数据能够更好地反映翼面流场的变化规律。The PSP(Pressure Sensitive Paint)measurements correction after the wind tunnel test is often implemented through the least square method,and it tends to neglect the chordwise and spanwise flow characteristics on the wing.By employing the IPS(Infinite Plate Spline)technique,a hybrid correction method and process for the PSP test results was presented.A full-span airplane model,with PSI(Pressure Scanner Instrument)and PSP on the upper and lower surfaces of the wing,was utilized to carry out the PSP test and PSI test simultaneously in a transonic wind tunnel with the 2.4 m test section.The pressure measurements were conducted at Ma=0.735 and in the angle of attack range from-6.38°to 10.59°.Test results indicate that the PSP data demonstrate a good agreement with PSI data.However,the PSP test system with only one camera shows a poor capacity to capture the aerodynamic field at the wing leading edge.The hybrid correction method for PSP results has proven to an effective approach,and the corrected data reveal that the hybrid correction can better deal with the pressure distribution characteristics of the full wing.

关 键 词：风洞试验 压力敏感涂料 压强分布 无限平板样条插值 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]