为了进一步研究弧形翼在小迎角超音速下的空气动力学特性,采用FLUENT软件对弧形翼的超音速三维绕流流场进行数值模拟。数值计算模型采用层流模型,离散格式为三阶MUSCL格式。计算来流马赫数取2.5~5.5,迎角取0°~8°。数值模拟结果给出了弧形翼流场激波波谱、表面压力分布等流场特性,重点分析零迎角下弧形翼产生升力的原因,得出了弧形翼在不同马赫数下,其升力系数、阻力系数随迎角变化的规律。

In order to further study the aerodynamic characteristics of wrap-around fin at supersonic speed, numerical simulation of flowfield over wrap-around fin was done by FLUENT software at small angle of attack at supersonic speeds in this paper. Laminar model was adopted in computational model with the third MUSCL scheme. The numerical simulation was performed at small angles of attack from 0 degree to 8 degree, with Mach number from 2.5 to 5.5. Results have shown the complicated flow structure of wrap-around fin, such as shock wave, surface pressure distribution. Possible sources of lift of wrap-around fin at zero angle of attack were analyzed. And the change trends of lift and drag with mach number and angle of attack were analyzed.