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为了研究超声速流动中底部排气减阻技术,采用AUSMPW+迎风格式、k-ω剪切应力输运(SST)湍流模型、8组分12反应化学动力学模型和二阶矩湍流燃烧模型求解三维带化学反应的Navier-Stokes方程。数值研究了超声速流动中底部排气流场,分析了底部排气形式对底部流场和减阻特性的影响规律和机理。计算结果表明:从减阻性能来看,随着排气参数的增大,采用边缘型排气得到的底压比呈增大趋势,而采用中心型排气得到的底压比呈先增大后减小的趋势;从流场结构来看,随着排气参数的增大,采用中心型排气的流场结构发生较大变化,前、后滞止点位置发生明显改变以至最后消失,初始回流区逐渐被后推以至消失,而采用边缘型排气的流场结构基本无重大变化,前滞止点位置始终不变,后滞止点位置后移,初始回流区始终存在。该文研究可为底排技术的工程应用提供参考。
In order to study the bottom exhaust drag reduction technology in supersonic flow, three-dimensional band (AUSMPW + upwind scheme, k-ω shear stress transport (SST) turbulence model, 8-component 12 reaction kinetic model and second- Navier-Stokes equations for chemical reactions. The flow field of bottom exhaust in supersonic flow was numerically studied, and the influence rule and mechanism of bottom exhaust on the bottom flow field and drag reduction were analyzed. The calculation results show that, from the drag reduction performance, with the increase of exhaust gas parameters, the pressure ratio obtained by the edge-type exhaust gas tends to increase, while the pressure ratio obtained by the center-type exhaust gas first increases And then decrease. With the increase of exhaust gas parameters, the structure of flow field with central exhaust gas changes greatly, the positions of front and rear stagnation points change obviously and finally disappear, The initial recirculation zone was gradually pushed back and even disappeared. However, the structure of flow field with edge-type exhaust did not change much, the position of the dead-end point remained the same, the position of the dead-end point was shifted backward, and the initial recirculation zone always existed. This study can provide a reference for engineering application of bottom row technology.