翼型采用近似边界条件的欧拉方程数值解

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翼型采用近似边界条件的欧拉方程数值解

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This paper presents an efficient numerical method for solving the Euler equations on rectilinear grids. Wall boundary conditions on the surface of an airfoil are implemented by using their first-order expansions on the airfoil chord line, which is placed along a grid line. However, the method is not restricted to flows with small disturbances since there are no restrictions on the magnitude of the velocity or pressure perturbations. The mathematical formulation and the numerical implementation of the wall boundary conditions in a finite-volume Euler code are described. Steady transonic flows are calculated about the NACA 0006, NACA 0012 and NACA 0015 airfoils, corresponding to thickness ratios of 6%, 12%, and 15%, respectively. The computed results, including surface pressure distributions, the lift coefficient, the wave drag coefficient, and the pitching moment coefficient, at angles of attack from 0° to 8° are compared with solutions at the same conditions by FLO52, a well-established Euler code using body-fitted curvilinear grids. Results demonstrate that the method yields acceptable accuracies even for the relatively thick NACA 0015 airfoil and at high angles of attack. This study establishes the potential of extending the method to computing unsteady fluid-structure interaction problems, where the use of a stationary rectilinear grid offers substantial advantages in both computer time and human work since it would not require the generation of time-dependent body-fitted grids.

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《西北工业大学学报》 |2003年第3期|253-258|共6页
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作者单位

Department of Aircraft Engineering, Northwestern Polytechnical University, Xi′an, 710072;

Department of Aircraft Engineering, Northwestern Polytechnical University, Xi′an, 710072;

Department of Mechanical and Aerospace Engineering, University of California, Irvine, CA 92697-3975, USA;

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原文格式 PDF
正文语种 chi
中图分类化学;
关键词
numerical simulation; airfoil; Euler equation; approximate boundary condition;

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1. 基于近似边界条件的翼型跨声速颤振数值模拟研究 [J] . 朱标 ,乔志德 ,高超 . 西北工业大学学报 . 2008,第002期
2. 绕任意刚性翼型,机翼非定常流动的跨声速欧拉方程解 [J] . 白俊强 . 空气动力学学报 . 1998,第002期
3. 二维翼型跨音速绕流欧拉方程数值计算 [J] . 王宗康 ,姜立男 . 气动研究与实验 . 1993,第001期
4. 基于高阶物面近似的自适应间断有限元法欧拉方程数值模拟 [J] . 孙强 ,吕宏强 ,伍贻兆 . 空气动力学学报 . 2015,第004期
5. 熵变量欧拉方程组跨超声速流SUPG有限元数值解 [J] . 张国富 ,张海明 . 空气动力学学报 . 1994,第004期
6. 基于近似边界条件定常跨音速翼型的欧拉方程数值计算 [C] . 张艳华 ,乔志德 ,刘峰 . 第十二届全国计算流体力学会议 . 2004
7. 基于近似边界条件的机翼跨音速欧拉方程数值模拟 [A] . 张艳华 . 2005

翼型采用近似边界条件的欧拉方程数值解

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