非定常导弹尾焰数值模拟

采用标准k-epsilon湍流模型对某型导弹高空飞行时的尾焰流场进行了模拟，对导弹飞行马赫数Ma由1.0变化为2.0和导弹尾喷管出口静压与大气静压比 由1.000变化为11.000的导弹尾焰流场分别进行了计算。分析了导弹飞行马赫数和静压比n对导弹尾焰产生的影响，并拟合出了相应的公式。

Numerical simulation of the unsteady-state missile plume

computations for a missile plumes flowfield were made using standard k-epsilon turbulence model in two parts. For one part, the mach number of the missile, as one of the missile model boundary conditions for computations, changes from 1.000 to 2.000. The another part, the missile plumes flowfield was simulated using the transient n (the static pressure ratio of missile nozzle exit to freestream) which changes from 1.000 to 11.000. The results can provide us the approximately data of missile plumes parameters under various operation conditions.