陈勇富, 曹长强, 文帅, 等. 高超声速剪敏液晶强反光抑制摩阻预示[J]. 实验流体力学, doi: 10.11729/syltlx20230154.
引用本文: 陈勇富, 曹长强, 文帅, 等. 高超声速剪敏液晶强反光抑制摩阻预示[J]. 实验流体力学, doi: 10.11729/syltlx20230154.
Chen Y F, Cao C Q, Wen S, et al. Suppressed strong reflection surface friction measurement by using shear sensitive liquid in hypersonic flow[J]. Journal of Experiments in Fluid Mechanics, doi: 10.11729/syltlx20230154.
Citation: Chen Y F, Cao C Q, Wen S, et al. Suppressed strong reflection surface friction measurement by using shear sensitive liquid in hypersonic flow[J]. Journal of Experiments in Fluid Mechanics, doi: 10.11729/syltlx20230154.

高超声速剪敏液晶强反光抑制摩阻预示

Suppressed strong reflection surface friction measurement by using shear sensitive liquid in hypersonic flow

  • 摘要: 高空高速下,准确的摩阻预示对飞行器气动性能至关重要。虽然光学非接触剪敏液晶技术在摩阻测量中优势明显,但仍存在诸多制约因素。针对剪敏液晶涂层摩阻测量技术在高超声速风洞试验中由于模型姿态和曲率变化引起的图像过曝光现象,研究了液晶涂层的表面光学特性,开展了基于光度学原理的光学系统设计,优化了液晶涂层的镜面反射因子响应特性,实现了不损失色彩还原度的强反光效应抑制,消除了液晶彩色图像中的过曝光干扰,建立了单次试验过程中获取多迎角变化的模型表面摩阻测量方法。以常规高超声速风洞为平台,开展了马赫数6来流条件下,迎角0°、4°、10°三角翼模型的典型摩阻测量试验。结果表明:基于光度优化的剪敏液晶摩阻测量方法,能够在一次试验中获取模型姿态变化条件下的摩阻分布及边界层流态特征,比传统方法的试验效率提升3倍以上,扩展了剪敏液晶涂层的风洞试验工程应用范围。

     

    Abstract: Precise surface friction measurement is important in hypersonic flight. Shear sensitive liquid crystal(SSLC) coating technique is an advantage method. However, there are some unsolved problems. Strong reflection occurs when poses and curvature vary. To conquer the challenge, the optical property of SSLC is studied. A novel optics system is designed based on photometry. Specular reflection effect reduces with color reproduction retained. Overexposure phenomena fade away, so we can acquire multiple friction distribution results from the wind tunnel experiment at one time. Experiments were carried out in the hypersonic wind tunnel of China Academy of Aerospace Aerodynamics. The test Mach number is 5.933, and the Reynolds number per unit based on the free-stream conditions is 0.95 × 107 m-1. In the experiment, the friction resistance was investigated at angles of attack that ranged from 0° to 10°. Results show that the suggested method is able to obtain the friction measurement results while the attack angles change. Compared with traditional means, the efficiency is a threefold improvement. The application range has extended in hypersonic wind tunnel experiments.

     

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