某飞行器的气动特性计算及仿真

Calculation and Simulation of Aircraft Aerodynamic Characteristics

为了研究飞行器在攻角范围为0°~15°时的气动特性,文中采用Gambit软件对飞行器进行物理建模,通过Fluent软件设置典型值对飞行器在某一马赫数和不同攻角下的气动力进行仿真计算,结果表明该飞行器的升力系数在攻角范围为0°~12°时逐渐变大,在攻角范围为12°~15°时减小;阻力系数和俯仰力矩系数随着攻角的增大逐渐增大.

The paper aims to study the aerodynamic characteristics of aircraft with the attack angle ranging from 0°to 15°.Firstly,the physical model of the aircraft is established with Gambit.Then,the software Fluent is adopted to conduct aircraft simulation at a speed in match and at different attack angles.The results indicate that the lift coefficient of aircraft increases when the attack angle ranges from0°to 12°,and decreases from 12°to 15°,and that the drag coefficient and pitching moment coefficient increase with the increasing aircraft attack angle.