航空学报 > 2022, Vol. 43 Issue (11): 526820-526820   doi: 10.7527/S1000-6893.2022.26820

基于在线加热涂层的宽速域转捩探测技术

王猛, 李玉军, 赵荣奂, 衷洪杰   

  1. 航空工业空气动力研究院 高速高雷诺数航空科技重点实验室, 沈阳 110034
  • 收稿日期:2021-12-14 修回日期:2021-12-20 出版日期:2022-11-15 发布日期:2022-01-18
  • 通讯作者: 衷洪杰,E-mail:hj.zhong@139.com E-mail:hj.zhong@139.com
  • 基金资助:
    民机专项

Transition detection technique for wide speed range by means of on-line heating coating

WANG Meng, LI Yujun, ZHAO Ronghuan, ZHONG Hongjie   

  1. Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research, AVIC Aerodynamics Research Institute, Shenyang 110034, China
  • Received:2021-12-14 Revised:2021-12-20 Online:2022-11-15 Published:2022-01-18
  • Supported by:
    Civil Aircraft Project

摘要: 针对跨/超声速层流机翼验证需求,提出基于在线加热涂层的转捩探测技术,通过提升原始数据信噪比以及探测判定结果可靠性,拓展转捩探测技术的速域适应范围。总结了跨声速层流机翼风洞和飞行试验转捩探测技术研究现状和存在的主要不足,提出一种3层结构的电加热涂层技术,给出绝缘层和电加热层的制备工艺,涂层总厚度可控制在40~60 μm,从而降低涂层对转捩和压力分布的影响。在亚跨声速条件下,开展翼段边界层转捩探测,使用电加热涂层技术将模型表面转捩前后的相对温差从2 K提高到4 K,温差增加1倍,同时利用电加热涂层技术实现了超声速后掠机翼转捩位置探测,形成了马赫数0.3~2.0工况范围内的转捩探测能力。在此基础上,形成了飞行试验转捩探测技术方案,给出了测试段机翼表面加热区功率、红外相机光学吊舱等详细设计方案。

关键词: 层流机翼, 转捩探测, 在线加热, 风洞试验, 飞行试验, 宽速域, 超声速, 跨声速

Abstract: A boundary layer transition detection technique by means of on-line heating coating is proposed for the verification requirements of transonic/supersonic laminar wings. The applicable speed range of transition detection is expanded by improving the signal-to-noise ratio and the experimental data reliability. The current status and the main shortcomings of the transition detection for transonic laminar wing in wind tunnel and flight test are summerized. A three layer electric heating coat structure is developed, and the preparation process of the insulation layer and the resistance coat layer presented. The total thickness of the heating coat can be controlled in 40-60 μm to reduce the influence of the heating coat on the boundary layer transition and pressure distribution. The first experiment was conducted in a transonic wind tunnel to measure the boundary layer transition on an airfoil. Compared with that of the traditional method, the temperature difference between the laminar and turbulent region measured by the electric heating technique was increased from 2 K to 4 K. The second experiment was conducted in a supersonic wind tunnel, where the transition location of a supersonic swept wing can be visualized with heating. The transition detection capability in the flow field of Mach number 0.3-2.0 was realized. On this basis, the transition detection technology scheme of flight tests is formed, and the detailed design schemes such as the power of the heating on the wing surface in the test section and the optical pod of the infrared camera are provided.

Key words: laminar wing, boundary transition detection, on-line heating, wind tunnel test, flight test, wide speed range, supersonic, transonic

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