论文部分内容阅读
针对采用多目标优化方法设计的超声速燃烧冲压发动机非对称喷管,采用RNGk-ε湍流模型和有限体积方法数值求解有组分的守恒形式Navier-Stokes方程,数值模拟喷管不同入口马赫数条件下的喷管流场和性能。计算结果表明:喷管入口马赫数的变化会对喷管内流参数带来一定影响,导致喷管的推力和升力同时增大或减小,飞行器的配平性能可能会受到一定影响。
For the asymmetric nozzle of supersonic combustion ramjet engine designed by multi-objective optimization method, the conservative form Navier-Stokes equations with components are numerically solved by RNGk-ε turbulence model and finite volume method. The nozzle flow field and performance. The calculation results show that the change of Mach number at the nozzle inlet will affect the nozzle flow parameters to a certain extent, causing the thrust and lift of the nozzle to increase or decrease at the same time. The trim performance of the aircraft may be affected to some extent.