摘要
通过对椭圆型方程进行抛物化差分离散，发展了一种快速抛物型方程贴体及与边界正交网格生成技术。采用该方法，生成了某歼击机全机真实外形三维ＯＣ型计算网格，并已成功地用于跨音速大迎角欧拉方程数值求解。实践表明，采用该方法能生成全机复杂外形高质量的计算网格。
Significant progress has been made in developing transonic flow computational methods for solving the Euler equations in the past decade in China. Because of the great generality of the flow solution methods, we can argue that the main difficulty in analyzing more complex configurations concerns the grid generation. Currently the most popular threedimensional grid generator is the elliptic equation technique. However, the elliptic equation technique has the disadvantage that the cost of numerically solving elliptic equations is considerable. On the other hand, in order to control the grid behavior, special source terms must be introduced. In this paper, authors have developed a fast method which can be called parabolic equation technique. Its merits are believed to be: 1. This method is able to produce a smooth grid, devoid of grid crossing, with direct marching from the body to the outer boundary. 2. Successful control of grid orthogonality on body is achieved by means of the introduction of algebraic grid prediction. 3. It has been demonstrated to produce very suitable grid for a complex aerodynamic configuration. 4. This method can produce grid for viscous flow and its speed is very fast. As an example, this gridgenerating method has been used in aerodynamic calculations of actual aircraft and found to give satisfactory results.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1997年第1期42-46,共5页
Journal of Northwestern Polytechnical University
基金
国家教委博士点基金
航空科学基金
关键词
抛物型方程
全机真实外形
飞机
计算网络
bodyfitted and bodynormal grid, parabolic equation technique, aircraft
