基于0.6米量级三声速风洞的压敏漆试验技术研究

  • 刘祥 ,
  • 熊健 ,
  • 黄辉 ,
  • 李永红 ,
  • 黄勇 ,
  • 王红彪 ,
  • 陈植
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  • 1. 中国空气动力研究与发展中心
    2. 中国空气动力研究与发展中心高速空气动力研究所
    3. 国防科学技术大学航天科学与工程学院宇航科学与工程系

收稿日期: 2019-04-15

  修回日期: 2020-04-01

  网络出版日期: 2020-04-03

基金资助

国家自然科学基金

Research on Experimental Technique of Pressure Sensitive Paint Based on 0.6m Trisonic Tunnel

  • LIU Xiang ,
  • XIONG Jian ,
  • HUANG Hui ,
  • LI Yong-Hong ,
  • HUANG Yong ,
  • WANG Hong-Biao ,
  • CHEN Zhi
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Received date: 2019-04-15

  Revised date: 2020-04-01

  Online published: 2020-04-03

摘要

基于0.6米暂冲式三声速风洞,建立了压敏漆(pressure sensitive paint,PSP)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自然科学基金项目“未来大型客机的减阻与激波控制”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帕,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。

本文引用格式

刘祥 , 熊健 , 黄辉 , 李永红 , 黄勇 , 王红彪 , 陈植 . 基于0.6米量级三声速风洞的压敏漆试验技术研究[J]. 航空学报, 0 : 0 -0 . DOI: 10.7527/S1000-6893.2020.23085

Abstract

Pressure-sensitive paint measurement system are established in 0.6m trisonic wind tunnel after subsystem synchronization control problem is resolved. Based on the established pressure-sensitive paint system, the effect of coating on surface pressure distribution, image filtering technology and the measurement stability and accuracy of pressure-sensitive paint system are studied. The system is applied to the wing surface pressure measurement test under future large passenger aircraft drag reduction and shock control project of the National Natural Science Foundation of China, and 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 design state. The research indicates, the changes in surface roughness and thickness caused by the lack of coating quality can significantly affect the pressure distribution, spray quality need strict control. Gaussian filtering with 8-pixel window and 3-times iteration gives better smoothing of pressure fluctuations without distortion. The pressure coefficient measurement root mean square deviation of the established pressure-sensitive paint system and pressure sensor is less than 0.022, pressure-sensitive paint system measurement accuracy is high. The design bump can effectively weaken the shock wave and improve the lift and drag characteristics of the wing in the design state and non-design state.
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