高速风洞支架干扰数值修正研究

Computational investigation of longitudinal support interferences in high speed wind tunnel

提出了一种计算高速风洞支架系统对飞行器模型纵向气动力干扰量的数值计算方法 ,从跨声速全位势积分方程出发 ,编制了适用于飞行器全机模型及其带支架情况下的跨声速绕流计算程序。通过对双垂尾模型和GBM 0 3模型两个算例的计算 ,讨论了尾支撑位置及其几何外形参数对模型气动力的影响 ,并对GBM 0 3模型带短支杆情况下的纵向实验结果进行了修正。表明该方法对于分析研究风洞模型支架干扰问题并进行支架干扰修正是可行的、有效的 ,可以作为选择尾支撑位置及其几何外形参数和对跨声速风洞纵向实验结果进行支架干扰修正的工具。

A field integral method has been applied to calculate model support interferences for transonic flows over models with embedded supersonic regions. The program based on the integral formulation of transonic full potential equation is presented to calculate the aerodynamic coefficients of the model with and without a horizontal sting (rear sting), and the difference between the aerodynamic coefficients of the two conditions is used to correct the support interference. In this paper, the distribution of the singularities of source and vorticity is based on panel method, and the field grid is divided by the means of penetrating grid, in which the body configuration is ignored and the intensity of the field sources in body is zero. The calculations have been carried out for two models: the model of double vertical tails on body and GBM-03 model. The results of the present method are compared to those given by earlier experimental data.