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Chen Xiaoping, Li Xinliang, Zhong Fengquan. THE OPTIMIZED REFERENCE ENTHALPY METHOD USING IN HIGH-SPEED TURBULENT CHANNEL FLOWS[J]. Chinese Journal of Theoretical and Applied Mechanics, 2013, 45(4): 614-618. DOI: 10.6052/0459-1879-12-308
Citation: Chen Xiaoping, Li Xinliang, Zhong Fengquan. THE OPTIMIZED REFERENCE ENTHALPY METHOD USING IN HIGH-SPEED TURBULENT CHANNEL FLOWS[J]. Chinese Journal of Theoretical and Applied Mechanics, 2013, 45(4): 614-618. DOI: 10.6052/0459-1879-12-308
shu

THE OPTIMIZED REFERENCE ENTHALPY METHOD USING IN HIGH-SPEED TURBULENT CHANNEL FLOWS

  • 1.

    State Key Lab. of High-temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

  • 2. School of Mechanical Engineering and Automation, Zhejiang Sci-Tech University, Zhejiang 310018, China

Funds: The project was supported by the National Natural Science Fundation of China (11072248), the Major State Basic Research Development Program of China (2009CB724100), the National Key Technologies R&D Program of China (2012AA01A304) and the CAS Program (KJCX2-EW-J01).
  • Received Date: March 05, 2013
  • Revised Date: April 07, 2013
    Graphical Abstract
    • Abstract
  • Direct numerical simulations of high-speed turbulent channel flows have been performed. The classic reference enthalpy method was evaluated and optimized by using the data with inflow Mach numbers of 3, 5, 6, 7, and 10. In fully developed turbulent flow, studies have shown that the classic reference enthalpy method is not applicable in high-speed channel flows. The wall heat flux predicted by the optimized reference enthalpy methods I and II are much better than the classic reference enthalpy method; moreover, the optimized reference enthalpy method II is more suitable, whose errors are within 10% compared with DNS. At the same time, the optimized reference enthalpy method II has been verified based on the experiment data of thermal environment of supersonic combustor.
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    • References (9)
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    陈小平, 李新亮, 樊菁. 变比热真实气体效应的高超声速槽道湍流直接数值模拟. 中国科学: 物理学 力学 天文学, 2011, 41(8): 969-979 (Chen Xiaoing, Li XinLiang, Fan Jing. Direct numerical simulation of hypersonic turbulent channel flow in thermally perfect gas. Scientia Sinica Phys, Mech & Astron, 2011, 41(8): 969-979 (in Chinese))
    袁涛, 李龙, 王晶等. 超声速燃烧隔离段热环境的实验测量与理论分析. 见:第四届高超声速科技学术会议, 2011. CSTAM 2011-2771 (Yuan Tao, Li Long, Fan Xuejun, et al. Measurement and calculation of thermal environment of supersonic combustor. In: The Proc. of the Fourth Hypersonic Technology Conference, 2011. CSTAM 2011-2771 (in Chinese))
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