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超音速战斗机发射导弹时,导弹发动机排放的燃气的温度很高。这种高温气体吸入进气道,使进气道里的气流温度陡然上升,并使进气道出口流场不均匀,致使发动机进口环境条件恶化,由此造成发动机喘振,甚至停车。采用计算流体力学方法,应用标准k-ε湍流模型和动态网格技术,对某型飞机发射导弹时的流场进行了模拟。计算分析了导弹射流对进气道性能的影响。数值计算结果反应了随着导弹移动进气道流场的变化情况,对于设计导弹发射点位置及进气道结构有一定的意义。
When the supersonic fighter jet fired missiles, the temperature of the gas emitted by the missile engine was high. The high-temperature gas is drawn into the air inlet, causing the temperature of the air flow in the air inlet to rise suddenly and make the inlet flow field uneven. As a result, the environmental conditions of the engine are deteriorated, causing the engine to surge and even stop. The computational fluid dynamics (CFD) method was used to simulate the flow field of a certain type of aircraft when it launched a missile using standard k-ε turbulence model and dynamic grid technique. The influence of missile jet on the performance of the air intake was calculated and analyzed. The numerical results reflect the changes of the flow field of the missile as the missile moves, which is of some significance for designing the location of the launching point of the missile and the structure of the intake duct.