Rotational axisymmetric mean flow and damping of acoustic waves in asolid propellant rocket.
Rotational axisymmetric mean flow and damping of acoustic waves in asolid propellant rocket.
复制标题
固体推进剂火箭中声波的旋转轴对称平均流量和阻尼。
作者：
F. Culick
虽然对于许多目的来说，火箭燃烧室中稳定流动的一维贴近是足够的，但有时需要更准确的信息。例如，对压力振荡稳定性的分析涉及流线的知识。通常的做法是在边界条件下使用势流的解，边界条件是没有流过头端且垂直于燃烧表面的匀速。由于马赫数通常很小，所以可以假定密度是恒定的；圆柱形腔室中的马赫数的结果是
.!LTHOUGH for many purposes the one-dimensional apft proximation to the steady flow in a rocket chamber is adequate, there are occasions when more precise information is required. For example, analysis of the stability of pressure oscillations involves knowledge of the streamlines. It has been common practice to use the solution for potential flow subject to the boundary conditions of no flow through the head end and uniform speed normal to the burning surface. Since the Mach number generally is very small, one may assume the density to be constant; the result for the Mach number in a cylindrical chamber is