为研究不同攻角、马赫数下火箭的气动特性,采用有限体积法,对某型火箭在亚跨超声速来流条件下的流场进行了数值模拟,给出了阻力系数、升力系数、俯仰力矩系数、升阻比以及压力中心随攻角、马赫数的变化规律,结果表明:小攻角和大攻角条件下,阻力系数、升力系数、俯仰力矩系数和压力中心随攻角表现出不同的特性,且与马赫数也有很大关系;不同马赫数下,升阻比最大值基本在22°~26°攻角范围内取得。

In order to investigate aerodynamic characteristics of rocket at different angle of attack and mach number, the finite volume method was used to simulate the flow field of rocket in subsonic, transonic and supersonic flow. The drag coefficient, lift coefficient, pitching moment coefficient, lift-drag ratio and center of pressure with variation angles of attack, mach numbers were given. The results indicate that the drag coefficient, lift coefficient, pitching moment coefficient and center of pressure perform differently at small angles of attack and big angles of attack and they also act differently with variety of mach numbers. The maximum of lift-drag ratio will be gained at 22°~26°angle of attack for different mach number.