复杂外形气动力计算的阻力修正方法

基于气动力计算的位流线化理论,发展了一种亚音速附面层阻力修正方法。采用联合流场求解方法获得复杂外形的表面压力分布,在此基础上,将绕复杂外形物体沿流向面元划分为片条,在片条上,把三维附面层转换为二维附面层,对二维附面层进行数值求解,得到附面层粘性阻力修正。算例表明,该方法计算量小,与实验和N-S数值解结果吻合较好。为复杂气动外形飞行器初期设计、方案选型及评估提供了较为理想的工程设计手段。

A Drag Correction Method of Aerodynamic Calculation for Complex Configuration

In this paper, a subsonic drag-prediction method with viscous correction based on of potential theory is presented. This method calculates viscous to improve the calculating results of drag with the unified field theory. In this method, 3-D boundary layer was superseded by the 2-D boundary layers to plot 3-D boundary layer of the complex configuration into slips along the flow direction. Analytic relations among the boundary variables can be founded on the integral solution. Adding up every slip drag, and considering the disturbance between boundary layers, the corrected total drag of the complex configuration can be attained. From the above, the good agreements with the experiments and numerical results indicate tiat the method in this paper can be used to assess the aerodynamic performance accurately and quickly.