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本文将粘性流场分析和数值优化方法耦合起来 ,发展了一种跨声速翼型设计方法 ,用以提高翼型在一个或多个设计点、在多种约束条件下的气动性能。由粘性流场分析程序计算得到的升力、阻力等气动参数构成目标函数 ,数值优化程序对其进行最小化。粘性流场分析采用了雷数平均N S方程 ,这比过去翼型设计中使用的全速势方程或Euler方程更能模拟流动的本质 ,因而设计结果的可靠性大大提高了。优化算法采用传统的拟牛顿法 (Quasi NewtonMethod)和序列无约束极小化方法 (SUMT)。算例研究表明 ,本文发展的跨声速翼型设计方法设计质量高 ,所需机时不多 ,有较大的工程应用价值。
In this paper, the viscous flow field analysis and the numerical optimization method are combined to develop a transonic airfoil design method to improve the aerodynamic performance of the airfoil at one or more design points under a variety of constraints. The aerodynamic parameters such as lift and drag calculated by the viscous flow field analysis program constitute the objective function, and the numerical optimization program minimizes it. The viscous flow field analysis uses the average Ns equation of thunder number, which simulates the nature of the flow more than the all-potential or Euler equations used in the past airfoil design. As a result, the reliability of the design results is greatly improved. The optimization algorithm uses the traditional Quasi Newton Method and the sequence unconstrained minimization method (SUMT). The case study shows that the design method of transonic airfoil developed in this paper is of high quality, less machine time and great engineering value.