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设计了一种新的无人飞行器气动外形布局,应用基于二次曲线的模线设计方法完成了飞行器气动外形建模,并对所建模型进行气动特性计算分析。将飞行器几何外形节点数据导入Gambit软件,生成气动特性计算所需的网格文件。应用Fluent软件,根据不同的飞行条件,选择合适的计算流体力学分析方法,对无人飞行器外形布局进行气动特性计算。主要讨论了在飞行马赫数为0.3、0.6和1.3时,对应不同飞行高度和迎角条件下飞行器的纵向气动特性,包括升力系数、阻力系数以及俯仰力矩系数。通过对计算结果的统计与分析,得出飞行器在不同飞行条件下的升阻比以及静稳定度,来判定其飞行性能以及飞行稳定性。经过计算与分析得出,所设计的飞行器外形布局符合飞行要求,并且具有良好的气动特性和稳定性。
A new aerodynamic configuration of UAV was designed. Aerodynamic profile modeling of the aircraft was completed by using the die design method based on quadratic curve. The aerodynamic characteristics of the model were calculated and analyzed. The aircraft geometry data is imported into Gambit software to generate the grid file needed for calculating the aerodynamic characteristics. Using Fluent software, according to different flight conditions, choose the appropriate computational fluid dynamics analysis method, the aerodynamic characteristics of UAV aircraft layout. The longitudinal aerodynamic characteristics of the aircraft at different flight altitudes and angles of attack including the lift coefficient, the drag coefficient and the pitch moment coefficient are mainly discussed when the flight Mach numbers are 0.3, 0.6 and 1.3. Through the statistics and analysis of the calculation results, the lift-drag ratio and the static stability of the aircraft under different flight conditions are obtained to determine its flight performance and flight stability. After calculation and analysis, the designed aircraft layout meets the flight requirements and has good aerodynamic characteristics and stability.