头部局部轮廓变形飞行器气动特性的研究

Study on Aerodynamic Characteristics of Aerocraft with Local Profile Deformation

针对智能细长体飞行器头部局部轮廓变形缩比模型,以通用流体计算软件FLUENT为计算平台,研究多种飞行器头部局部轮廓变形方案在不同来流速度下的气动特性,分析飞行器所受到的气动升力、阻力和偏航力矩系数得出定性变化规律,再通过低速风洞试验分析验证多种头部鼓包和变截面变形方案对飞行器气动特性的定量影响,由大量的数值模拟仿真和风洞试验结果总结出了飞行器头部局部轮廓变形位置和形状对飞行器机动特性影响的定量规律。

This paper worked on the intelligent aerocraft scale model with local profile deformation.Based on the general purposed computational fluid dynamics software or FLUENT,it analyzed the aerodynamic characteristics of several deformation projects with different air speed,and also illustrated the qualitative variation of aerodynamic lift,drag and yawing moment coefficient.Then it tested the quantitative rule of aerodynamic characteristics by wind tunnel experiments under different deformation projects.Finally,it was concluded that aerodynamic characteristics variation affected by local profile deformation according to a mass of numerical simulation and wind tunnel experiment results.