摘要
采用雷诺平均的Navier-Stokes方程,对接网格技术和TRIP（TRI sonic Platform）软件,数值模拟了CT-1标模大迎角静态气动特性。来流马赫数0.5,迎角0°～100°,侧滑角0°和5°,在与1.2 m跨声速风洞试验结果对比的基础上,重点讨论了对流项离散方法、湍流模型、远场距离和不同尾部处理形式对CT-1标模大迎角静态气动特性影响。研究结果表明,不同尾部处理形式对大迎角静态气动特性数值模拟结果影响显著,模拟试验的尾部支杆是对比大迎角静态测力试验结果与计算结果的基本要求。
The static aerodynamic characteristics of CT-1 model at high angles of attack are simulated with patched grid and CFD software TRI sonic platform（TRIP）,and the Reynolds averaged Navier-Stokes equation is adopted.The free stream condition is Mach number 0.5,the angles of attack are in the range of 0°～100°,and the angles of sideslip are 0° and 5°.On the base of comparison with the test data obtained from 1.2 m transonic wind tunnel in CARDC,the influence of different methods of advection term,turbulent models,far field distance and tail supporter are emphatically discussed.Numerical results are summarized,which indicate that different styles of supporter have large influence on numerical results of static aerodynamic characteristics at high angles of attack,and the key point of comparison between test data and CFD results is to simulate the supporter of test model faithfully.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第4期859-865,共7页
Acta Aeronautica et Astronautica Sinica
关键词
CT-1标模
大迎角
静态气动特性
尾支杆
CT-1 model
high angle of attack
static aerodynamic characteristic
tail supporter
