| 跨声速翼型绕流计算边界层反方法的研究 |
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| 引用本文： | 李友荣,张玉伦,陈作斌. 跨声速翼型绕流计算边界层反方法的研究[J]. 空气动力学学报, 1991, 0(2) |
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| 作者姓名： | 李友荣 张玉伦 陈作斌 |
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| 作者单位： | 中国空气动力研究与发展中心(李友荣，张玉伦)，中国空气动力研究与发展中心(陈作斌) |
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| 摘 要： | 本文用有限差分方法,通过有粘/无粘迭代计算了二元翼型的跨声速绕流问题。在边界层粘性区域内考虑了层流、转捩及湍流流动,当边界层内出现分离时,使用边界层反方法,采用代数湍流模型。算例表明,对激波/边界层弱干扰和强干扰情况,该方法的结果与风洞实验结果吻合良好,对于求解边界层小分离流场是一种好的近似方法。
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| 关 键 词： | 有限差分 边界层 反方法 |
THE STUDY OF INVERSE BOUNDARY LAYER ALGORITHM FOR TRANSONIC FLOWS OVER AEROFOILS |
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| Li Yourong Zhang Yulun Chen Zuobin. THE STUDY OF INVERSE BOUNDARY LAYER ALGORITHM FOR TRANSONIC FLOWS OVER AEROFOILS[J]. Acta Aerodynamica Sinica, 1991, 0(2) |
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| Authors: | Li Yourong Zhang Yulun Chen Zuobin |
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| Affiliation: | China Aerodynamics Research and Development Center |
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| Abstract: | A viscous/inviscid interaction model is used for the solution of transonic flows over two-demensional aerofoils based on finite difference method. Laminar, transition, turbulent flows are taken into account in the viscous layer. Inverse boundary layer algorithm is used when the flow is separated. Algebraic model is adopted for the turbulent flow. The results show that the present method is in good agreement with the wind tunnel experiment for both weak and strong interaction cases between the shock wave and boundary layer. The presenod method is also suitable for the boundary layer with separation bubbles. |
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| Keywords: | finite difference boundary layer inverse algorithm. |
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