来流马赫数对射流矢量喷管内流场影响的动态模拟

摘要

Taking the 2D convergent-divergent nozzle as a research object, the 2D unsteady Reynolds average N-S equation and RNG k-e turbulence model was utilized to study the unsteady flow field of fluidic thrust vectoring nozzle based shock control. The influence of continual variation of the incoming flow Mach number on the flow field in the nozzle is analyzed. The changing regularity of nozzle thrust performance was derived. The results show that the incoming flow Mach number causes the change of pressure round the nozzle exit, and influences the internal flow characteristics of the vectoring nozzle by the interaction of nozzle boundary layer and shock; in the subsonic free flow, with the increase of incoming flow Mach number, the thrust increases; in the transonic flow, the side thrust and axial thrust decrease hardly; when the Mach number is supersonic velocity, the thrust de-clines with the increase of Mach number; and the thrust vector angle and thrust coefficient are same as the changing regularity of side thrust and axial thrust.%以二维拉瓦尔喷管为对象，利用非定常雷诺平均N—S方程和RNGκ-ε两方程湍流模型对激波控制的射流推力矢量喷管非定常流场进行研究，分析了来流马赫数连续变化对喷管流场的影响，得出喷管推力性能的变化规律。结果表明：在亚声速来流中，轴向力随飞行马赫数增加而小幅上升，侧向力变化不大；在跨声速来流中，轴向推力和侧向推力都急剧下降；来流马赫数为超声速时，推力随马赫数的增加而减小。推力矢量角和推力系数分别与侧向力和轴向力的变化规律相似。