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Direct numerical simulation methods of hypersonic flat-plate boundary layer in thermally perfect gas

Direct numerical simulation methods of hypersonic flat-plate boundary layer in thermally perfect gas
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摘要 High-temperature effects alter the physical and transport properties of air such as vibrational excitation in a thermally perfect gas,and this factor should be considered in order to compute the flow field correctly.Herein,for the thermally perfect gas,a simple method of direct numerical simulation on flat-plat boundary layer is put forward,using the equivalent specific heat ratio instead of constant specific heat ratio in the N-S equations and flux splitting form of a calorically perfect gas.The results calculated by the new method are consistent with that by solving the N-S equations of a thermally perfect gas directly.The mean flow has the similarity,and consistent to the corresponding Blasius solution,which confirms that satisfactory results can be obtained basing on the Blasius solution as the mean flow directly in stability analysis.The amplitude growth curve of small disturbance is introduced at the inlet by using direct numerical simulation,which is consistent with that obtained by linear stability theory.It verified that the equation established and the simulation method is correct. High-temperature effects alter the physical and transport properties of air such as vibrational excitation in a thermally perfect gas, and this factor should be considered in order to compute the flow field correctly. Herein, for the thermally perfect gas, a simple method of direct numerical simulation on flat-plat boundary layer is put forward, using the equivalent specific heat ratio instead of constant specific heat ratio in the N-S equations and flux splitting form of a calorically perfect gas. The results cal- culated by the new method are consistent with that by solving the N-S equations of a thermally perfect gas directly. The mean flow has the similarity, and consistent to the corresponding Blasius solution, which confirms that satisfactory results can be obtained basing on the Blasius solution as the mean flow directly in stability analysis. The amplitude growth curve of small disturbance is introduced at the inlet by using direct numerical simulation, which is consistent with that obtained by linear sta- bility theory. It verified that the equation established and the simulation method is correct.
出处 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2014年第2期336-344,共9页 中国科学:物理学、力学、天文学(英文版)
基金 supported by the National Nature Science Foundation of China(Grant Nos.11172203 and 91216111) the National Basic Research Program of China(Grant No.2009CB724103)
关键词 hypersonic fiat-plate boundary layer direct numerical simulation variable specific heat equivalent specific heat ratio 平板边界层 完全气体 数值模拟方法 超音速 直接数值模拟 线性稳定性理论 理想气体 比热容比
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