超声速流动中底部排气形式对减阻性能的影响
收稿日期: 2013-09-27
修回日期: 2013-12-05
网络出版日期: 2013-12-23
基金资助
总装备部十二五预研项目（404040302）；江苏省普通高校研究生科研创新计划项目（CXLX13_202）
Effect of Base Bleed Type on Drag Reduction Performance in Supersonic Flow
Received date: 2013-09-27
Revised date: 2013-12-05
Online published: 2013-12-23
Supported by
Pre-research Project of General Equipment Department During the Period of 12th Five Year (404040302); Project of Jiangsu Innovation Program for Graduate Education (CXLX13-202)
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。
卓长飞 , 武晓松 , 封锋 . 超声速流动中底部排气形式对减阻性能的影响[J]. 航空学报, 2014 , 35(8) : 2144 -2155 . DOI: 10.7527/S1000-6893.2013.0488
In order to research on the base bleed for drag reduction in a supersonic flow, three dimensional Navier-Stokes equations with chemical reactions are solved by the high-accuracy and high-resolution upwind scheme (AUSMPW +), k-ω shear stress transport (SST) turbulence model, the 8 species and 12 reaction kinetics model, and the second-order turbulent combustion model. The base bleed flow field is numerically simulated in a supersonic flow. The rule and mechanism are analyzed of the effect of base bleed type on flow structure and drag reduction performance in the supersonic flow. Calculation results show that: from the drag reduction performance point of view, with the increase of base bleed parameters, the base pressure ratio tends to continuously increase using the edge type, while the base pressure ratio using the center type tends to increase first, and then decrease; from the flow structure point of view, with the increase of base bleed parameters, the flow structure using the center type changes greatly, the position of the front and rear stagnation point changes significantly and finally disappears, and the initial recirculation zone is gradually pushed until it disappears, while there is basically no significant change in the flow structure with the edge type-the position of front stagnation point is always the same, the position of rear stagnation point is pushed backward, and the initial recirculation zone always exists. These results can provide useful reference for the engineering application of base bleed projectiles.
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