宇航学报 ›› 2017, Vol. 38 ›› Issue (7): 758-765.doi: 10.3873/j.issn.1000-1328.2017.07.012

• 飞行器试验与发射 • 上一篇    下一篇

激波风洞边界层强制转捩试验研究

李强,张扣立,庄宇,赵金山   

  1. 中国空气动力研究与发展中心超高速所,绵阳 621000
  • 收稿日期:2017-01-22 修回日期:2017-05-11 出版日期:2017-07-15 发布日期:2017-07-25
  • 基金资助:

    国家重点研发计划“大科学装置前沿研究”重点专项(2016YFA0401201)

Experimental Investigation on Forced Boundary Layer Transition in Shock Tunnel

LI Qiang, ZHANG Kou li, ZHUANG Yu, ZHAO Jin shan   

  1. Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2017-01-22 Revised:2017-05-11 Online:2017-07-15 Published:2017-07-25

摘要:

针对升力体模型设计了涡流发生器,在中国空气动力研究与发展中心(CARDC)Φ2 m激波风洞上开展风洞试验,研究了高超声速边界层强制转捩问题。试验来流名义马赫数分别为10、12,单位雷诺数分别为2.4×10 6/m、2.1×10 6/m,模型攻角10°。试验中应用铂薄膜热流传感器技术和温敏热图(TSP)技术测量了模型表面热流,证明涡流发生器实现了模型边界层强制转捩,使Φ2 m激波风洞拥有了模拟高马赫数低雷诺数湍流边界层的能力。试验结果表明,不同形状不同高度涡流发生器对边界层完全转捩成湍流后的热流影响不明显,由此可提出一种新的激波风洞试验方法,即利用涡流发生器开展相同来流条件下不同边界层流态对模型表面热流等边界层参数分布影响的试验 研究 。

关键词: 激波风洞, 涡流发生器, 强制转捩, 湍流模拟

Abstract:

The experiment of the hypersonic boundary-layer forced-transition is carried out in a Φ2 m shock tunnel which is affiliated to China Aerodynamics Research and Development Center (CARDC). The forced-transition trip is a vortex generator which is designed and mounted on a lifting body model. The test nominal Mach numbers are 10 and 12, the unit Reynolds numbers are 2.4×10 6 /m and 2.1×10 6/m respectively, and the angle of attack is 10°. The model surface heat transfer is measured by the thin film thermal gauges and temperature sensitive paint (TSP) technique. Tests results show that the initial motivation of the artificial transition is triggered. Thus, it is able to carry out the measurement campaigns which require turbulent boundary layer in high Mach number and low Reynolds number flows. A series of vortex generators, differing from shape and height, are investigated in this project. By comparing heat transfer downstream of these vortex generators, no significant difference is found in regions where artificial transition is totally completed. And also, the results give us confidence to carry out the experimental study aiming to find out some different flow characteristics such as heat transfer distribution under laminar and turbulent boundary layer in the identical inflow condition.

Key words: Shock tunnel, Vortex generator, Forced transition, Turbulent flow simulation

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