Effect of non-equilibrium condensation on lift divergence Mach number at transonic speeds

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• 作者：Heung Kyun Jeon ; Seung Min Choi…
• 关键词：Angle of attack ; Lift divergence Mach number ; Moist air ; Non ; equilibrium condensation ; Shock stall ; Transonic speeds ; Supersonic bubble ; TVD scheme
• 刊名：Journal of Mechanical Science and Technology
• 出版年：2015
• 出版时间：July 2015
• 年：2015
• 卷：29
• 期：7
• 页码：2883-2888
• 全文大小：1,324 KB
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• 作者单位：Heung Kyun Jeon (1)
  Seung Min Choi (2)
  Young Doo Kwon (3)
  Soon Bum Kwon (3)
  
  1. Fire Safety Management Dept., Daegu Health College, 15, Yeongsong-ro, Buk-gu, Daegu, 702-722, Korea
  2. Gyeongbuk Institute for Advancement of Eco-Friendly Auto Parts Technology, 27, Sampoong-ro, Gyeongsan, 712-210, Korea
  3. School of Mechanical Engineering, Kyungpook National University, 80, Daehak-ro, Buk-gu, Daegu, 702-701, Korea
  
• 刊物类别：Engineering
• 刊物主题：Mechanical Engineering
  Structural Mechanics
  Control Engineering
  Industrial and Production Engineering
  
• 出版者：The Korean Society of Mechanical Engineers
• ISSN：1976-3824

文摘

In the present paper, the effects of non-equilibrium condensation on the lift divergence Mach number with the angle of attack in a transonic 2-D moist air flow of NACA0012 are investigated using a numerical analysis with a total variation diminishing scheme. In the case of T 0 = 298 K and α = 3°, the lift divergence Mach number M ld decreases with increasing Ф 0 up to 40%, whereas beyond Ф 0 = 40%, the lift divergence Mach number is nearly constant at M ld = 0.75. On the other hand, for the case of α = 6°, M ld increases with increasing Ф 0 up to 47%, and then M ld begins to decrease with an increase in Ф 0. Because of the attenuating effect of non-equilibrium condensation on the shock stall, for the case of α = 3°, C L generally decreases with an increase in Ф 0, whereas for M?= 0.85, which is appreciably larger than the lift divergence Mach number, C L increases with an increase in Ф 0. In the case of M?= 0.85, regardless of Ф 0, it is shown that the location of the maximum Mach number at the upper wall side is nearly constant at x/c = 0.4. It is found that the Mach number for the minimum C L decreases with an increase in Ф 0.