鸭式布局冲压增程制导炮弹三维流场模拟与数值分析

Three-dimensional Flow Field Simulation and Numerical Analysis of Ramjet Extended-range Guided Projectile With Canard Layout

为研究鸭式布局冲压增程制导炮弹的流场与气动特性,根据其在冲压工作状态和被动飞行状态时对应的气动外形,应用分块网格划分方法和Realizable k-ε湍流模型对2种工作状态分别进行了三维流场模拟与数值计算分析,对不同马赫数下炮弹的流场与气动特性进行了研究。结果表明:在超声速条件下,相同攻角时阻力系数和升力系数都随马赫数增大而减小;同一工况下,与相同外形参数但不采用冲压形式的鸭式布局制导炮弹(参考弹)相比,冲压工作状态下阻力系数约大50.5%,升力系数约小35.7%,被动飞行状态下阻力系数约大42.9%,升力系数约小11.9%;被动飞行状态采用中心锥组件向前推进的形式对减小阻力是有利的。研究结果为鸭式布局冲压增程制导炮弹的气动外形设计与性能分析提供了一定的理论基础与参考。

In order to study the flow field and aerodynamic characteristics of the canard ramjet extended-range guided projectile,according to the aerodynamic characteristics of the projectile under the ramjet state and passive flight state,the 3 D flow field simulation and numerical calculation analysis were carried out by using the sliding meshing technique and Realizable k-ε model respectively. The flow field and aerodynamic characteristics of projectile at different Mach numbers were studied. The results show that under supersonic conditions,both the drag coefficient and the lift coefficient decrease with the increase of Mach number at the same angle of attack. Under the same working condition,compared with the canard layout guided projectile with the same shape parameters but without ramjet structure(reference projectile),the drag coefficient is about 50.5% higher and the lift coefficient is about 35.7% smaller in the ramjet state,42.9% higher and 11.9% smaller in the passive flight state. The forward thrust form of the central cone assembly in the passive flight state is beneficial to reduce the drag. The research results provide a theoretical basis and reference for the aerdynamic shape design and performance analysis of canard ramjet extended-range guided projectile.