某飞行器的气动特性计算及仿真  

Calculation and Simulation of Aircraft Aerodynamic Characteristics

作　　者：倪原[1] 戴凯[1] 刘智平[1] 张辉[1] 

机构地区：[1]西安工业大学电子信息工程学院,西安710021

出　　处：《西安工业大学学报》2015年第3期210-215,共6页Journal of Xi’an Technological University

摘　　要：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.

关 键 词：攻角 物理建模 飞行器 气动仿真 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]